NACA 23021 (naca23021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 1,000,000 Max Cl/Cd: 55.84 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23021-il-1000000-n5.txt Download as CSV file: xf-naca23021-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2824 0.07044 0.06544 -0.0492 1.0000 0.0343
-19.500 -1.2859 0.06693 0.06187 -0.0501 1.0000 0.0347
-19.250 -1.2892 0.06350 0.05838 -0.0510 1.0000 0.0350
-19.000 -1.2916 0.06022 0.05503 -0.0517 1.0000 0.0353
-18.750 -1.2929 0.05709 0.05185 -0.0523 1.0000 0.0357
-18.500 -1.2924 0.05422 0.04892 -0.0528 1.0000 0.0361
-18.250 -1.2905 0.05155 0.04620 -0.0532 1.0000 0.0365
-18.000 -1.2878 0.04899 0.04358 -0.0535 1.0000 0.0369
-17.750 -1.2845 0.04655 0.04108 -0.0537 1.0000 0.0374
-17.500 -1.2795 0.04431 0.03879 -0.0538 1.0000 0.0378
-17.250 -1.2734 0.04222 0.03664 -0.0539 1.0000 0.0381
-17.000 -1.2668 0.04022 0.03458 -0.0538 1.0000 0.0384
-16.750 -1.2624 0.03806 0.03238 -0.0536 1.0000 0.0389
-16.500 -1.2564 0.03611 0.03039 -0.0534 1.0000 0.0394
-16.250 -1.2488 0.03435 0.02859 -0.0530 1.0000 0.0399
-15.750 -1.2310 0.03122 0.02538 -0.0521 1.0000 0.0410
-15.500 -1.2207 0.02983 0.02396 -0.0515 1.0000 0.0415
-15.250 -1.2094 0.02857 0.02266 -0.0508 1.0000 0.0420
-15.000 -1.1976 0.02739 0.02144 -0.0500 1.0000 0.0425
-14.750 -1.1861 0.02624 0.02026 -0.0491 1.0000 0.0430
-14.500 -1.1755 0.02509 0.01909 -0.0481 1.0000 0.0437
-14.250 -1.1640 0.02406 0.01803 -0.0469 1.0000 0.0444
-14.000 -1.1522 0.02312 0.01708 -0.0456 1.0000 0.0450
-13.750 -1.1400 0.02230 0.01623 -0.0442 1.0000 0.0457
-13.500 -1.1285 0.02155 0.01546 -0.0425 1.0000 0.0463
-13.250 -1.1188 0.02088 0.01476 -0.0403 1.0000 0.0469
-13.000 -1.1018 0.02025 0.01410 -0.0393 0.9985 0.0475
-12.750 -1.0791 0.01945 0.01330 -0.0396 0.9952 0.0486
-12.500 -1.0543 0.01876 0.01260 -0.0401 0.9921 0.0497
-12.250 -1.0318 0.01814 0.01197 -0.0400 0.9866 0.0507
-12.000 -1.0076 0.01758 0.01140 -0.0401 0.9806 0.0517
-11.750 -0.9839 0.01708 0.01088 -0.0399 0.9737 0.0525
-11.500 -0.9633 0.01652 0.01031 -0.0392 0.9644 0.0539
-11.250 -0.9441 0.01603 0.00981 -0.0380 0.9538 0.0553
-11.000 -0.9252 0.01560 0.00934 -0.0366 0.9425 0.0568
-10.750 -0.9067 0.01520 0.00892 -0.0351 0.9297 0.0583
-10.500 -0.8888 0.01479 0.00848 -0.0335 0.9169 0.0604
-10.250 -0.8702 0.01443 0.00808 -0.0319 0.9031 0.0626
-10.000 -0.8518 0.01408 0.00768 -0.0302 0.8861 0.0656
-9.500 -0.8142 0.01336 0.00693 -0.0270 0.8517 0.0770
-9.250 -0.7950 0.01303 0.00660 -0.0255 0.8367 0.0851
-9.000 -0.7752 0.01280 0.00633 -0.0239 0.8208 0.0916
-8.750 -0.7559 0.01256 0.00608 -0.0222 0.8056 0.0971
-8.500 -0.7340 0.01238 0.00585 -0.0210 0.7912 0.1013
-8.250 -0.7118 0.01217 0.00560 -0.0199 0.7753 0.1063
-8.000 -0.6883 0.01198 0.00539 -0.0190 0.7606 0.1109
-7.750 -0.6653 0.01177 0.00516 -0.0180 0.7480 0.1165
-7.500 -0.6415 0.01159 0.00495 -0.0171 0.7342 0.1219
-7.250 -0.6179 0.01138 0.00474 -0.0163 0.7214 0.1290
-7.000 -0.5949 0.01116 0.00451 -0.0153 0.7081 0.1391
-6.500 -0.5502 0.01056 0.00404 -0.0131 0.6857 0.1759
-6.250 -0.5274 0.01026 0.00382 -0.0122 0.6746 0.1978
-5.750 -0.4801 0.00978 0.00347 -0.0104 0.6515 0.2381
-5.250 -0.4295 0.00951 0.00323 -0.0092 0.6252 0.2655
-5.000 -0.4037 0.00944 0.00313 -0.0086 0.6079 0.2768
-4.750 -0.3784 0.00936 0.00303 -0.0080 0.5907 0.2883
-4.500 -0.3517 0.00931 0.00296 -0.0076 0.5756 0.2974
-4.250 -0.3256 0.00922 0.00287 -0.0071 0.5623 0.3074
-4.000 -0.2990 0.00919 0.00280 -0.0067 0.5485 0.3167
-3.750 -0.2731 0.00909 0.00273 -0.0062 0.5348 0.3296
-3.500 -0.2467 0.00905 0.00266 -0.0058 0.5207 0.3406
-3.250 -0.2205 0.00900 0.00261 -0.0053 0.5071 0.3521
-3.000 -0.1935 0.00896 0.00256 -0.0050 0.4943 0.3608
-2.750 -0.1671 0.00894 0.00252 -0.0046 0.4809 0.3716
-2.500 -0.1405 0.00890 0.00249 -0.0042 0.4684 0.3840
-2.250 -0.1137 0.00887 0.00246 -0.0039 0.4579 0.3975
-2.000 -0.0874 0.00883 0.00243 -0.0034 0.4459 0.4114
-1.750 -0.0605 0.00881 0.00242 -0.0031 0.4355 0.4237
-1.500 -0.0337 0.00882 0.00242 -0.0028 0.4234 0.4369
-1.250 -0.0072 0.00880 0.00241 -0.0024 0.4115 0.4504
-1.000 0.0193 0.00884 0.00242 -0.0020 0.3979 0.4631
-0.750 0.0463 0.00884 0.00243 -0.0017 0.3866 0.4767
-0.500 0.0730 0.00887 0.00245 -0.0014 0.3755 0.4875
-0.250 0.1001 0.00890 0.00247 -0.0011 0.3640 0.4980
0.000 0.1272 0.00896 0.00250 -0.0008 0.3515 0.5062
0.250 0.1534 0.00904 0.00254 -0.0004 0.3368 0.5161
0.500 0.1802 0.00913 0.00258 -0.0001 0.3220 0.5252
0.750 0.2065 0.00919 0.00263 0.0003 0.3082 0.5353
1.000 0.2332 0.00929 0.00269 0.0006 0.2966 0.5442
1.250 0.2595 0.00939 0.00276 0.0009 0.2841 0.5526
1.500 0.2860 0.00947 0.00283 0.0013 0.2736 0.5627
1.750 0.3122 0.00958 0.00291 0.0016 0.2636 0.5726
2.000 0.3386 0.00965 0.00299 0.0020 0.2544 0.5844
2.250 0.3647 0.00978 0.00308 0.0023 0.2444 0.5941
2.500 0.3906 0.00988 0.00318 0.0028 0.2342 0.6050
2.750 0.4165 0.01002 0.00328 0.0031 0.2231 0.6148
3.000 0.4417 0.01015 0.00340 0.0037 0.2121 0.6261
3.500 0.4921 0.01043 0.00366 0.0047 0.1912 0.6520
3.750 0.5167 0.01061 0.00381 0.0053 0.1793 0.6643
4.000 0.5406 0.01081 0.00398 0.0060 0.1666 0.6775
4.250 0.5638 0.01103 0.00417 0.0068 0.1527 0.6928
4.500 0.5854 0.01129 0.00441 0.0079 0.1365 0.7133
4.750 0.6058 0.01162 0.00470 0.0091 0.1168 0.7342
5.000 0.6166 0.01248 0.00533 0.0119 0.0642 0.7529
5.250 0.6386 0.01272 0.00561 0.0129 0.0595 0.7697
5.500 0.6614 0.01292 0.00585 0.0138 0.0574 0.7839
6.000 0.7033 0.01332 0.00633 0.0162 0.0548 0.8127
6.250 0.7236 0.01355 0.00661 0.0175 0.0537 0.8271
6.500 0.7452 0.01380 0.00689 0.0185 0.0529 0.8411
6.750 0.7668 0.01403 0.00718 0.0195 0.0524 0.8543
7.000 0.7883 0.01430 0.00749 0.0205 0.0519 0.8666
7.250 0.8093 0.01458 0.00781 0.0215 0.0513 0.8806
7.500 0.8297 0.01488 0.00816 0.0226 0.0508 0.8932
7.750 0.8499 0.01522 0.00853 0.0237 0.0504 0.9056
8.000 0.8689 0.01557 0.00893 0.0250 0.0499 0.9178
8.250 0.8878 0.01596 0.00936 0.0263 0.0495 0.9303
8.500 0.9060 0.01639 0.00981 0.0276 0.0491 0.9435
8.750 0.9246 0.01686 0.01032 0.0287 0.0487 0.9550
9.000 0.9440 0.01739 0.01087 0.0295 0.0483 0.9653
9.250 0.9649 0.01794 0.01144 0.0299 0.0479 0.9750
9.500 0.9892 0.01848 0.01199 0.0296 0.0478 0.9817
9.750 1.0129 0.01906 0.01259 0.0293 0.0476 0.9884
10.000 1.0375 0.01967 0.01322 0.0288 0.0474 0.9932
10.250 1.0634 0.02035 0.01393 0.0278 0.0471 0.9968
10.500 1.0885 0.02108 0.01467 0.0269 0.0469 1.0000
10.750 1.0968 0.02174 0.01536 0.0292 0.0467 1.0000
11.000 1.1076 0.02248 0.01612 0.0309 0.0465 1.0000
11.250 1.1196 0.02329 0.01696 0.0322 0.0464 1.0000
11.500 1.1317 0.02420 0.01789 0.0333 0.0462 1.0000
11.750 1.1441 0.02517 0.01889 0.0342 0.0460 1.0000
12.000 1.1561 0.02622 0.01997 0.0350 0.0458 1.0000
12.250 1.1674 0.02738 0.02116 0.0357 0.0457 1.0000
12.500 1.1784 0.02862 0.02244 0.0363 0.0455 1.0000
12.750 1.1889 0.02995 0.02382 0.0368 0.0453 1.0000
13.000 1.1984 0.03141 0.02531 0.0373 0.0452 1.0000
13.250 1.2069 0.03301 0.02695 0.0376 0.0451 1.0000
13.500 1.2148 0.03472 0.02871 0.0379 0.0449 1.0000
13.750 1.2219 0.03655 0.03059 0.0381 0.0448 1.0000
14.000 1.2280 0.03854 0.03263 0.0381 0.0447 1.0000
14.250 1.2327 0.04071 0.03485 0.0381 0.0445 1.0000
14.500 1.2363 0.04306 0.03726 0.0380 0.0444 1.0000
14.750 1.2386 0.04560 0.03986 0.0377 0.0443 1.0000
15.000 1.2398 0.04833 0.04265 0.0374 0.0442 1.0000
15.250 1.2397 0.05123 0.04562 0.0369 0.0441 1.0000
15.500 1.2381 0.05437 0.04883 0.0364 0.0440 1.0000
15.750 1.2353 0.05772 0.05225 0.0357 0.0439 1.0000
16.000 1.2312 0.06127 0.05588 0.0349 0.0438 1.0000
16.250 1.2260 0.06498 0.05967 0.0340 0.0438 1.0000
16.500 1.2200 0.06887 0.06363 0.0330 0.0437 1.0000
16.750 1.2126 0.07298 0.06781 0.0319 0.0436 1.0000
17.000 1.2041 0.07724 0.07216 0.0307 0.0435 1.0000
17.250 1.1957 0.08155 0.07655 0.0294 0.0434 1.0000
17.500 1.1877 0.08585 0.08092 0.0281 0.0433 1.0000
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