Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Reynolds number: 200,000 Max Cl/Cd: 76.52 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-root-ns-200000.txt Download as CSV file: xf-prandtl-d-root-ns-200000.csv |
XFOIL Version 6.96
Calculated polar for: Prandtl-D root - NASA Preliminary Research Aerod
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.5306 0.23265 0.23000 0.0574 1.0000 0.0187
-19.750 -0.5224 0.22900 0.22634 0.0558 1.0000 0.0190
-19.500 -0.5148 0.22573 0.22306 0.0541 1.0000 0.0195
-19.250 -0.5076 0.22259 0.21992 0.0521 1.0000 0.0199
-19.000 -0.5005 0.21946 0.21678 0.0502 1.0000 0.0206
-18.750 -0.4934 0.21633 0.21364 0.0481 1.0000 0.0215
-18.500 -0.4864 0.21321 0.21051 0.0460 1.0000 0.0222
-18.250 -0.4804 0.21025 0.20754 0.0436 1.0000 0.0233
-18.000 -0.4776 0.20836 0.20565 0.0405 1.0000 0.0236
-17.750 -0.4750 0.20654 0.20382 0.0377 1.0000 0.0237
-17.500 -0.4684 0.20280 0.20009 0.0356 1.0000 0.0239
-17.250 -0.4540 0.19745 0.19473 0.0350 1.0000 0.0244
-17.000 -0.4454 0.19436 0.19163 0.0333 1.0000 0.0249
-16.750 -0.4373 0.19141 0.18868 0.0314 1.0000 0.0256
-16.500 -0.4297 0.18851 0.18577 0.0294 1.0000 0.0264
-16.250 -0.4224 0.18557 0.18283 0.0273 1.0000 0.0273
-16.000 -0.4153 0.18264 0.17988 0.0251 1.0000 0.0284
-15.750 -0.4095 0.17993 0.17717 0.0227 1.0000 0.0294
-15.500 -0.4088 0.17837 0.17560 0.0194 1.0000 0.0299
-15.250 -0.4111 0.17745 0.17468 0.0161 1.0000 0.0301
-15.000 -0.3938 0.17123 0.16847 0.0155 1.0000 0.0307
-14.750 -0.3817 0.16794 0.16517 0.0142 1.0000 0.0317
-14.500 -0.3733 0.16522 0.16245 0.0123 1.0000 0.0327
-14.250 -0.3658 0.16250 0.15972 0.0103 1.0000 0.0338
-14.000 -0.3591 0.15976 0.15698 0.0081 1.0000 0.0351
-13.750 -0.3541 0.15722 0.15444 0.0056 1.0000 0.0364
-13.500 -0.3574 0.15612 0.15333 0.0022 1.0000 0.0373
-13.250 -0.3648 0.15576 0.15298 -0.0008 1.0000 0.0376
-13.000 -0.3692 0.15472 0.15192 -0.0033 1.0000 0.0377
-12.750 -0.3408 0.14687 0.14407 -0.0035 1.0000 0.0386
-12.500 -0.3296 0.14396 0.14116 -0.0046 1.0000 0.0395
-12.250 -0.3227 0.14151 0.13871 -0.0063 1.0000 0.0406
-12.000 -0.3158 0.13867 0.13587 -0.0083 1.0000 0.0419
-11.750 -0.3100 0.13564 0.13284 -0.0107 1.0000 0.0436
-11.500 -0.3086 0.13272 0.12992 -0.0139 1.0000 0.0455
-11.250 -0.3169 0.13050 0.12771 -0.0185 0.9815 0.0464
-11.000 -0.3182 0.12714 0.12434 -0.0223 0.9675 0.0467
-10.750 -0.3209 0.12371 0.12090 -0.0247 0.9549 0.0468
-10.500 -0.3052 0.11934 0.11650 -0.0204 0.9365 0.0481
-10.250 -0.2977 0.11736 0.11449 -0.0181 0.9222 0.0496
-10.000 -0.4168 0.11910 0.11612 -0.0195 1.0000 0.0470
-9.750 -0.3948 0.11502 0.11202 -0.0172 1.0000 0.0484
-9.500 -0.3823 0.11153 0.10855 -0.0189 1.0000 0.0493
-9.250 -0.3702 0.10815 0.10519 -0.0210 1.0000 0.0511
-9.000 -0.3594 0.10412 0.10114 -0.0255 0.9640 0.0546
-8.750 -0.3620 0.09967 0.09667 -0.0321 0.9421 0.0569
-8.500 -0.3338 0.09119 0.08830 -0.0302 0.8688 0.0581
-8.250 -0.3186 0.08757 0.08462 -0.0268 0.8613 0.0592
-8.000 -0.3093 0.08450 0.08153 -0.0261 0.8534 0.0603
-7.750 -0.3065 0.08118 0.07818 -0.0262 0.8466 0.0615
-7.500 -0.3060 0.07736 0.07435 -0.0272 0.8400 0.0627
-7.250 -0.3084 0.07329 0.07028 -0.0286 0.8332 0.0639
-7.000 -0.3156 0.06895 0.06592 -0.0303 0.8276 0.0654
-6.750 -0.3260 0.06397 0.06097 -0.0338 0.8203 0.0667
-6.500 -0.3469 0.05898 0.05594 -0.0373 0.8144 0.0676
-6.250 -0.3883 0.05077 0.04730 -0.0449 0.8071 0.0698
-6.000 -0.4512 0.04012 0.03525 -0.0472 0.8192 0.0380
-5.750 -0.4400 0.03655 0.03146 -0.0455 0.8138 0.0368
-5.500 -0.4281 0.03256 0.02705 -0.0442 0.8060 0.0359
-5.250 -0.4150 0.02922 0.02316 -0.0420 0.8003 0.0355
-5.000 -0.3964 0.02674 0.02019 -0.0405 0.7939 0.0362
-4.750 -0.3749 0.02533 0.01827 -0.0390 0.7875 0.0376
-4.500 -0.3547 0.02288 0.01548 -0.0375 0.7828 0.0386
-4.250 -0.3295 0.02148 0.01398 -0.0371 0.7755 0.0402
-4.000 -0.3050 0.02043 0.01276 -0.0362 0.7703 0.0423
-3.750 -0.2791 0.01970 0.01183 -0.0355 0.7647 0.0456
-3.500 -0.2540 0.01846 0.01051 -0.0350 0.7585 0.0496
-3.250 -0.2294 0.01769 0.00965 -0.0340 0.7538 0.0543
-3.000 -0.2040 0.01679 0.00873 -0.0335 0.7477 0.0622
-2.750 -0.1790 0.01611 0.00808 -0.0328 0.7422 0.0782
-2.500 -0.1547 0.01554 0.00747 -0.0319 0.7380 0.1014
-2.250 -0.1279 0.01524 0.00720 -0.0318 0.7316 0.1199
-2.000 -0.1020 0.01492 0.00686 -0.0313 0.7264 0.1385
-1.750 -0.0771 0.01455 0.00654 -0.0306 0.7225 0.1653
-1.500 -0.0512 0.01415 0.00637 -0.0305 0.7162 0.2084
-1.250 -0.0269 0.01368 0.00613 -0.0299 0.7111 0.2716
-1.000 -0.0035 0.01324 0.00591 -0.0289 0.7073 0.3505
-0.750 0.0199 0.01284 0.00590 -0.0283 0.7014 0.4454
-0.500 0.1321 0.01135 0.00591 -0.0445 0.6966 0.8862
-0.250 0.1603 0.01173 0.00610 -0.0438 0.6927 0.9664
0.000 0.2477 0.01176 0.00591 -0.0562 0.6871 1.0000
0.250 0.2738 0.01181 0.00583 -0.0559 0.6818 1.0000
0.500 0.2992 0.01185 0.00571 -0.0554 0.6778 1.0000
0.750 0.3260 0.01196 0.00575 -0.0554 0.6726 1.0000
1.000 0.3525 0.01204 0.00576 -0.0552 0.6675 1.0000
1.250 0.3783 0.01210 0.00569 -0.0548 0.6633 1.0000
1.500 0.4047 0.01223 0.00576 -0.0547 0.6585 1.0000
1.750 0.4315 0.01235 0.00584 -0.0546 0.6533 1.0000
2.000 0.4574 0.01243 0.00584 -0.0542 0.6491 1.0000
2.250 0.4834 0.01255 0.00589 -0.0539 0.6450 1.0000
2.500 0.5102 0.01272 0.00607 -0.0539 0.6393 1.0000
2.750 0.5363 0.01282 0.00612 -0.0536 0.6348 1.0000
3.000 0.5620 0.01293 0.00614 -0.0531 0.6313 1.0000
3.250 0.5887 0.01314 0.00641 -0.0532 0.6253 1.0000
3.500 0.6148 0.01326 0.00651 -0.0529 0.6205 1.0000
3.750 0.6405 0.01335 0.00653 -0.0524 0.6168 1.0000
4.000 0.6668 0.01358 0.00684 -0.0524 0.6108 1.0000
4.250 0.6927 0.01369 0.00695 -0.0521 0.6056 1.0000
4.500 0.7184 0.01376 0.00696 -0.0515 0.6016 1.0000
4.750 0.7442 0.01399 0.00729 -0.0514 0.5950 1.0000
5.000 0.7700 0.01407 0.00738 -0.0510 0.5897 1.0000
5.250 0.7957 0.01416 0.00743 -0.0505 0.5852 1.0000
5.500 0.8210 0.01434 0.00772 -0.0503 0.5778 1.0000
5.750 0.8467 0.01436 0.00772 -0.0497 0.5726 1.0000
6.000 0.8718 0.01446 0.00791 -0.0493 0.5645 1.0000
6.250 0.8972 0.01421 0.00757 -0.0484 0.5555 1.0000
6.500 0.9217 0.01395 0.00732 -0.0475 0.5419 1.0000
6.750 0.9461 0.01382 0.00723 -0.0468 0.5285 1.0000
7.000 0.9703 0.01373 0.00719 -0.0460 0.5149 1.0000
7.250 0.9942 0.01363 0.00709 -0.0452 0.4982 1.0000
7.500 1.0177 0.01364 0.00712 -0.0444 0.4807 1.0000
7.750 1.0409 0.01376 0.00729 -0.0438 0.4629 1.0000
8.000 1.0632 0.01392 0.00746 -0.0429 0.4412 1.0000
8.250 1.0851 0.01418 0.00773 -0.0421 0.4210 1.0000
8.500 1.1060 0.01450 0.00806 -0.0411 0.3977 1.0000
8.750 1.1243 0.01498 0.00845 -0.0398 0.3661 1.0000
9.000 1.1385 0.01570 0.00899 -0.0380 0.3236 1.0000
9.250 1.1488 0.01663 0.00972 -0.0358 0.2824 1.0000
9.500 1.1548 0.01773 0.01062 -0.0331 0.2434 1.0000
9.750 1.1564 0.01894 0.01164 -0.0297 0.2068 1.0000
10.000 1.1516 0.02033 0.01280 -0.0256 0.1703 1.0000
10.250 1.1416 0.02160 0.01394 -0.0208 0.1462 1.0000
10.500 1.1371 0.02296 0.01518 -0.0171 0.1240 1.0000
10.750 1.1342 0.02448 0.01660 -0.0142 0.1016 1.0000
11.000 1.1328 0.02611 0.01813 -0.0117 0.0835 1.0000
11.250 1.1294 0.02803 0.01993 -0.0093 0.0583 1.0000
11.500 1.1246 0.03021 0.02197 -0.0072 0.0439 1.0000
11.750 1.1256 0.03207 0.02389 -0.0056 0.0361 1.0000
12.000 1.1256 0.03412 0.02597 -0.0040 0.0300 1.0000
12.250 1.1289 0.03595 0.02787 -0.0028 0.0269 1.0000
12.500 1.1294 0.03808 0.03004 -0.0016 0.0249 1.0000
12.750 1.1325 0.04004 0.03211 -0.0006 0.0241 1.0000
13.000 1.1340 0.04221 0.03438 0.0003 0.0227 1.0000
13.250 1.1353 0.04445 0.03672 0.0011 0.0223 1.0000
13.500 1.1360 0.04681 0.03918 0.0018 0.0217 1.0000
13.750 1.1361 0.04931 0.04178 0.0024 0.0213 1.0000
14.000 1.1349 0.05203 0.04459 0.0029 0.0208 1.0000
14.250 1.1350 0.05465 0.04731 0.0033 0.0207 1.0000
14.500 1.1346 0.05737 0.05011 0.0036 0.0205 1.0000
14.750 1.1333 0.06022 0.05301 0.0040 0.0202 1.0000
15.000 1.1342 0.06283 0.05568 0.0044 0.0200 1.0000
15.250 1.1356 0.06529 0.05818 0.0051 0.0196 1.0000
15.500 1.1402 0.06756 0.06054 0.0055 0.0191 1.0000
15.750 1.1456 0.06969 0.06276 0.0061 0.0189 1.0000
16.000 1.1509 0.07192 0.06510 0.0065 0.0185 1.0000
16.250 1.1580 0.07385 0.06713 0.0073 0.0184 1.0000
16.500 1.1656 0.07581 0.06922 0.0083 0.0184 1.0000
16.750 1.1711 0.07817 0.07173 0.0088 0.0183 1.0000
17.000 1.1756 0.08079 0.07450 0.0094 0.0184 1.0000
17.250 1.1763 0.08402 0.07793 0.0095 0.0184 1.0000
17.500 1.1731 0.08790 0.08201 0.0091 0.0184 1.0000
17.750 1.1681 0.09210 0.08641 0.0084 0.0185 1.0000
18.000 1.1607 0.09677 0.09129 0.0073 0.0187 1.0000
18.250 1.1508 0.10193 0.09665 0.0057 0.0188 1.0000
18.500 1.1383 0.10768 0.10260 0.0037 0.0190 1.0000
18.750 1.1256 0.11360 0.10871 0.0012 0.0191 1.0000
19.000 1.1099 0.12032 0.11562 -0.0019 0.0192 1.0000
19.250 1.0940 0.12728 0.12275 -0.0054 0.0193 1.0000
19.500 1.0798 0.13416 0.12978 -0.0089 0.0195 1.0000
19.750 1.0635 0.14187 0.13765 -0.0132 0.0196 1.0000
20.000 1.0437 0.15117 0.14717 -0.0193 0.0199 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns)