NACA 23021 (naca23021-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 500,000 Max Cl/Cd: 50.55 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23021-il-500000-n5.txt Download as CSV file: xf-naca23021-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23021
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.1335 0.08855 0.08311 -0.0445 1.0000 0.0408
-19.500 -1.1343 0.08519 0.07967 -0.0456 1.0000 0.0413
-19.250 -1.1353 0.08177 0.07618 -0.0467 1.0000 0.0417
-19.000 -1.1348 0.07859 0.07293 -0.0477 1.0000 0.0421
-18.750 -1.1345 0.07541 0.06967 -0.0486 1.0000 0.0426
-18.500 -1.1353 0.07215 0.06634 -0.0496 1.0000 0.0430
-18.250 -1.1377 0.06873 0.06288 -0.0505 1.0000 0.0434
-18.000 -1.1392 0.06544 0.05953 -0.0513 1.0000 0.0439
-17.750 -1.1395 0.06233 0.05637 -0.0521 1.0000 0.0443
-17.500 -1.1386 0.05943 0.05342 -0.0526 1.0000 0.0448
-17.250 -1.1370 0.05664 0.05056 -0.0532 1.0000 0.0453
-17.000 -1.1348 0.05394 0.04779 -0.0536 1.0000 0.0458
-16.750 -1.1313 0.05144 0.04522 -0.0539 1.0000 0.0464
-16.500 -1.1270 0.04907 0.04279 -0.0541 1.0000 0.0469
-16.250 -1.1217 0.04684 0.04048 -0.0543 1.0000 0.0475
-16.000 -1.1206 0.04423 0.03783 -0.0544 1.0000 0.0480
-15.750 -1.1177 0.04187 0.03543 -0.0544 1.0000 0.0486
-15.500 -1.1132 0.03973 0.03324 -0.0542 1.0000 0.0492
-15.250 -1.1075 0.03777 0.03123 -0.0539 1.0000 0.0498
-15.000 -1.1008 0.03595 0.02936 -0.0535 1.0000 0.0505
-14.750 -1.0930 0.03428 0.02764 -0.0530 1.0000 0.0512
-14.500 -1.0844 0.03275 0.02606 -0.0524 1.0000 0.0519
-14.250 -1.0753 0.03132 0.02458 -0.0517 1.0000 0.0527
-14.000 -1.0690 0.02974 0.02297 -0.0508 1.0000 0.0535
-13.750 -1.0612 0.02836 0.02157 -0.0497 1.0000 0.0543
-13.500 -1.0527 0.02714 0.02031 -0.0484 1.0000 0.0552
-13.250 -1.0436 0.02604 0.01918 -0.0470 1.0000 0.0561
-13.000 -1.0346 0.02507 0.01818 -0.0453 1.0000 0.0570
-12.750 -1.0263 0.02422 0.01729 -0.0432 1.0000 0.0580
-12.500 -1.0228 0.02332 0.01639 -0.0404 1.0000 0.0590
-12.250 -1.0206 0.02257 0.01563 -0.0371 1.0000 0.0602
-12.000 -1.0059 0.02179 0.01483 -0.0360 0.9979 0.0618
-11.500 -0.9552 0.02018 0.01321 -0.0376 0.9914 0.0664
-11.250 -0.9318 0.01948 0.01251 -0.0377 0.9859 0.0693
-11.000 -0.9075 0.01877 0.01183 -0.0380 0.9803 0.0734
-10.750 -0.8834 0.01813 0.01121 -0.0381 0.9742 0.0789
-10.500 -0.8606 0.01753 0.01064 -0.0379 0.9662 0.0855
-10.250 -0.8366 0.01700 0.01013 -0.0376 0.9585 0.0921
-10.000 -0.8152 0.01650 0.00963 -0.0369 0.9486 0.0980
-9.750 -0.7944 0.01604 0.00918 -0.0358 0.9381 0.1030
-9.500 -0.7737 0.01561 0.00873 -0.0346 0.9267 0.1084
-9.250 -0.7555 0.01519 0.00830 -0.0329 0.9124 0.1138
-9.000 -0.7363 0.01483 0.00791 -0.0313 0.8978 0.1194
-8.750 -0.7181 0.01443 0.00750 -0.0295 0.8831 0.1258
-8.500 -0.6998 0.01411 0.00716 -0.0277 0.8682 0.1326
-8.250 -0.6822 0.01378 0.00683 -0.0258 0.8543 0.1417
-8.000 -0.6640 0.01343 0.00649 -0.0239 0.8404 0.1544
-7.750 -0.6451 0.01303 0.00615 -0.0223 0.8258 0.1716
-7.500 -0.6252 0.01266 0.00583 -0.0208 0.8121 0.1910
-7.250 -0.6045 0.01236 0.00555 -0.0194 0.7976 0.2094
-7.000 -0.5828 0.01207 0.00530 -0.0182 0.7831 0.2276
-6.750 -0.5608 0.01181 0.00508 -0.0171 0.7702 0.2460
-6.500 -0.5378 0.01160 0.00489 -0.0160 0.7563 0.2626
-6.250 -0.5138 0.01143 0.00472 -0.0152 0.7430 0.2765
-6.000 -0.4900 0.01128 0.00455 -0.0143 0.7299 0.2886
-5.750 -0.4643 0.01117 0.00442 -0.0137 0.7178 0.2984
-5.500 -0.4401 0.01103 0.00427 -0.0128 0.7057 0.3090
-5.250 -0.4147 0.01092 0.00414 -0.0122 0.6927 0.3193
-5.000 -0.3899 0.01080 0.00401 -0.0115 0.6809 0.3300
-4.750 -0.3643 0.01070 0.00390 -0.0109 0.6685 0.3399
-4.500 -0.3395 0.01059 0.00379 -0.0101 0.6550 0.3524
-4.250 -0.3151 0.01051 0.00368 -0.0093 0.6386 0.3645
-4.000 -0.2895 0.01044 0.00359 -0.0087 0.6222 0.3756
-3.750 -0.2645 0.01036 0.00350 -0.0080 0.6080 0.3872
-3.250 -0.2136 0.01023 0.00337 -0.0068 0.5804 0.4129
-3.000 -0.1883 0.01018 0.00331 -0.0061 0.5673 0.4255
-2.750 -0.1623 0.01017 0.00326 -0.0056 0.5528 0.4381
-2.500 -0.1368 0.01012 0.00322 -0.0050 0.5393 0.4503
-2.250 -0.1111 0.01012 0.00319 -0.0044 0.5260 0.4630
-2.000 -0.0854 0.01009 0.00317 -0.0038 0.5121 0.4771
-1.750 -0.0597 0.01008 0.00315 -0.0033 0.4991 0.4892
-1.500 -0.0336 0.01011 0.00315 -0.0028 0.4862 0.5003
-1.250 -0.0074 0.01010 0.00314 -0.0023 0.4746 0.5105
-1.000 0.0184 0.01015 0.00315 -0.0018 0.4622 0.5211
-0.750 0.0450 0.01016 0.00316 -0.0014 0.4509 0.5303
-0.500 0.0708 0.01020 0.00318 -0.0008 0.4392 0.5410
-0.250 0.0970 0.01025 0.00320 -0.0004 0.4260 0.5509
0.000 0.1227 0.01029 0.00323 0.0001 0.4136 0.5615
0.500 0.1747 0.01041 0.00331 0.0011 0.3892 0.5811
0.750 0.2004 0.01051 0.00337 0.0016 0.3762 0.5920
1.000 0.2259 0.01055 0.00342 0.0021 0.3636 0.6036
1.250 0.2519 0.01065 0.00349 0.0026 0.3520 0.6148
1.500 0.2767 0.01074 0.00356 0.0032 0.3389 0.6258
1.750 0.3027 0.01083 0.00364 0.0036 0.3264 0.6369
2.000 0.3275 0.01093 0.00373 0.0043 0.3141 0.6485
2.500 0.3774 0.01115 0.00394 0.0055 0.2909 0.6749
2.750 0.4021 0.01129 0.00406 0.0061 0.2809 0.6876
3.000 0.4271 0.01140 0.00419 0.0067 0.2708 0.7009
3.250 0.4512 0.01155 0.00433 0.0074 0.2608 0.7144
3.500 0.4754 0.01168 0.00448 0.0082 0.2513 0.7320
4.000 0.5226 0.01196 0.00483 0.0099 0.2331 0.7712
4.250 0.5464 0.01211 0.00502 0.0106 0.2247 0.7869
4.500 0.5698 0.01232 0.00521 0.0115 0.2155 0.8008
4.750 0.5935 0.01249 0.00541 0.0122 0.2071 0.8148
5.000 0.6162 0.01272 0.00563 0.0132 0.1978 0.8277
5.250 0.6387 0.01296 0.00585 0.0141 0.1878 0.8415
5.500 0.6601 0.01323 0.00612 0.0152 0.1760 0.8544
5.750 0.6807 0.01352 0.00638 0.0165 0.1654 0.8664
6.000 0.6991 0.01383 0.00667 0.0182 0.1538 0.8793
6.250 0.7165 0.01421 0.00701 0.0200 0.1403 0.8917
6.500 0.7327 0.01471 0.00743 0.0218 0.1240 0.9048
6.750 0.7427 0.01558 0.00813 0.0245 0.0899 0.9175
7.000 0.7526 0.01648 0.00891 0.0271 0.0665 0.9303
7.250 0.7712 0.01700 0.00942 0.0283 0.0631 0.9422
7.500 0.7930 0.01751 0.00994 0.0289 0.0612 0.9518
7.750 0.8133 0.01804 0.01048 0.0296 0.0597 0.9620
8.000 0.8383 0.01863 0.01108 0.0293 0.0584 0.9688
8.250 0.8611 0.01917 0.01163 0.0294 0.0576 0.9772
8.500 0.8883 0.01978 0.01226 0.0285 0.0568 0.9821
8.750 0.9132 0.02043 0.01293 0.0279 0.0561 0.9881
9.000 0.9386 0.02115 0.01367 0.0271 0.0555 0.9926
9.250 0.9652 0.02194 0.01448 0.0258 0.0549 0.9960
9.500 0.9902 0.02284 0.01539 0.0248 0.0543 0.9998
9.750 0.9931 0.02356 0.01614 0.0278 0.0540 1.0000
10.000 0.9965 0.02440 0.01700 0.0307 0.0537 1.0000
10.250 1.0015 0.02537 0.01800 0.0329 0.0533 1.0000
10.500 1.0086 0.02642 0.01908 0.0347 0.0531 1.0000
10.750 1.0181 0.02748 0.02017 0.0359 0.0529 1.0000
11.000 1.0278 0.02862 0.02136 0.0370 0.0527 1.0000
11.250 1.0372 0.02988 0.02266 0.0379 0.0525 1.0000
11.500 1.0462 0.03125 0.02408 0.0386 0.0522 1.0000
11.750 1.0545 0.03276 0.02563 0.0392 0.0520 1.0000
12.000 1.0619 0.03441 0.02733 0.0397 0.0518 1.0000
12.250 1.0686 0.03618 0.02916 0.0400 0.0516 1.0000
12.500 1.0746 0.03809 0.03113 0.0402 0.0514 1.0000
12.750 1.0797 0.04015 0.03324 0.0404 0.0512 1.0000
13.000 1.0840 0.04236 0.03551 0.0404 0.0511 1.0000
13.250 1.0874 0.04473 0.03794 0.0403 0.0509 1.0000
13.500 1.0900 0.04726 0.04053 0.0400 0.0507 1.0000
13.750 1.0916 0.04994 0.04328 0.0397 0.0506 1.0000
14.000 1.0923 0.05279 0.04620 0.0392 0.0504 1.0000
14.250 1.0924 0.05577 0.04924 0.0387 0.0503 1.0000
14.500 1.0920 0.05886 0.05240 0.0380 0.0502 1.0000
14.750 1.0911 0.06204 0.05565 0.0373 0.0500 1.0000
15.000 1.0901 0.06526 0.05894 0.0365 0.0499 1.0000
15.250 1.0888 0.06859 0.06233 0.0357 0.0498 1.0000
15.500 1.0870 0.07200 0.06580 0.0348 0.0497 1.0000
15.750 1.0858 0.07535 0.06921 0.0338 0.0495 1.0000
16.000 1.0846 0.07870 0.07262 0.0329 0.0494 1.0000
16.250 1.0835 0.08210 0.07608 0.0319 0.0493 1.0000
16.500 1.0835 0.08534 0.07937 0.0309 0.0492 1.0000
16.750 1.0830 0.08867 0.08275 0.0298 0.0491 1.0000
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