AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 200,000 Max Cl/Cd: 73.5 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-9-il-200000.txt Download as CSV file: xf-ah21-9-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5012 0.08699 0.08349 -0.0263 1.0000 0.0409
-8.000 -0.5113 0.08385 0.08042 -0.0269 1.0000 0.0418
-7.750 -0.5231 0.08072 0.07737 -0.0277 1.0000 0.0422
-7.500 -0.5299 0.07600 0.07264 -0.0326 1.0000 0.0431
-7.000 -0.5349 0.06823 0.06453 -0.0373 1.0000 0.0442
-6.750 -0.5400 0.06196 0.05815 -0.0378 1.0000 0.0448
-6.500 -0.5353 0.05776 0.05409 -0.0364 1.0000 0.0461
-6.250 -0.5278 0.05524 0.05158 -0.0350 1.0000 0.0476
-6.000 -0.5191 0.05227 0.04853 -0.0344 1.0000 0.0501
-5.750 -0.5028 0.04989 0.04551 -0.0352 1.0000 0.0569
-5.500 -0.4953 0.04371 0.03919 -0.0354 1.0000 0.0588
-5.250 -0.4816 0.04102 0.03656 -0.0345 1.0000 0.0614
-5.000 -0.4645 0.03820 0.03324 -0.0344 1.0000 0.0723
-4.750 -0.4482 0.03583 0.03099 -0.0337 1.0000 0.0768
-4.500 -0.4286 0.03305 0.02783 -0.0334 1.0000 0.0873
-4.250 -0.4080 0.03108 0.02555 -0.0330 1.0000 0.0999
-4.000 -0.3670 0.02271 0.01582 -0.0312 1.0000 0.0415
-3.750 -0.3411 0.02084 0.01357 -0.0305 1.0000 0.0420
-3.500 -0.3155 0.01931 0.01174 -0.0297 1.0000 0.0425
-3.250 -0.2898 0.01781 0.00998 -0.0290 1.0000 0.0425
-3.000 -0.2649 0.01671 0.00874 -0.0282 1.0000 0.0432
-2.750 -0.2406 0.01596 0.00789 -0.0274 1.0000 0.0444
-2.500 -0.2165 0.01475 0.00673 -0.0269 1.0000 0.0494
-2.250 -0.1925 0.01416 0.00613 -0.0262 1.0000 0.0525
-2.000 -0.1684 0.01373 0.00561 -0.0255 1.0000 0.0570
-1.750 -0.1437 0.01309 0.00504 -0.0251 1.0000 0.0771
-1.500 -0.1236 0.01059 0.00507 -0.0245 1.0000 0.6538
-1.250 -0.1120 0.01018 0.00537 -0.0199 1.0000 0.8818
-1.000 -0.0737 0.01007 0.00519 -0.0224 1.0000 1.0000
-0.750 -0.0507 0.01023 0.00519 -0.0218 1.0000 1.0000
-0.500 -0.0279 0.01041 0.00525 -0.0213 1.0000 1.0000
-0.250 0.0092 0.01073 0.00546 -0.0237 0.9960 1.0000
0.000 0.0491 0.01104 0.00566 -0.0266 0.9905 1.0000
0.250 0.0906 0.01136 0.00591 -0.0297 0.9849 1.0000
0.500 0.1296 0.01158 0.00608 -0.0324 0.9784 1.0000
0.750 0.1725 0.01180 0.00627 -0.0357 0.9721 1.0000
1.000 0.2122 0.01191 0.00636 -0.0383 0.9641 1.0000
1.250 0.2594 0.01200 0.00646 -0.0423 0.9576 1.0000
1.500 0.2994 0.01192 0.00641 -0.0447 0.9476 1.0000
1.750 0.3453 0.01174 0.00630 -0.0481 0.9382 1.0000
2.000 0.4001 0.01135 0.00599 -0.0531 0.9297 1.0000
2.250 0.4438 0.01089 0.00564 -0.0556 0.9175 1.0000
2.500 0.4907 0.01026 0.00513 -0.0586 0.9043 1.0000
2.750 0.5332 0.00964 0.00462 -0.0604 0.8861 1.0000
3.000 0.5704 0.00916 0.00423 -0.0613 0.8592 1.0000
3.250 0.6108 0.00877 0.00389 -0.0628 0.8096 1.0000
3.500 0.6505 0.00885 0.00357 -0.0639 0.6878 1.0000
3.750 0.6622 0.00987 0.00372 -0.0601 0.5156 1.0000
4.000 0.6697 0.01119 0.00415 -0.0562 0.3421 1.0000
4.250 0.6816 0.01261 0.00477 -0.0536 0.1894 1.0000
4.500 0.6988 0.01379 0.00550 -0.0519 0.1156 1.0000
4.750 0.7188 0.01474 0.00629 -0.0505 0.0868 1.0000
5.000 0.7391 0.01570 0.00714 -0.0491 0.0700 1.0000
5.250 0.7607 0.01664 0.00812 -0.0478 0.0607 1.0000
5.500 0.7817 0.01811 0.00956 -0.0466 0.0547 1.0000
5.750 0.8058 0.01895 0.01053 -0.0457 0.0491 1.0000
6.000 0.8294 0.02040 0.01197 -0.0451 0.0449 1.0000
6.250 0.8555 0.02263 0.01438 -0.0445 0.0426 1.0000
6.500 0.8807 0.02420 0.01622 -0.0437 0.0406 1.0000
6.750 0.9040 0.02550 0.01774 -0.0427 0.0371 1.0000
7.000 0.9265 0.02758 0.02012 -0.0417 0.0355 1.0000
7.250 0.9468 0.03021 0.02305 -0.0403 0.0342 1.0000
7.500 0.9604 0.03475 0.02796 -0.0385 0.0327 1.0000
7.750 0.9716 0.03748 0.03127 -0.0357 0.0312 1.0000
8.000 0.9788 0.04196 0.03622 -0.0329 0.0314 1.0000
8.250 0.9891 0.04660 0.04113 -0.0309 0.0329 1.0000
15.250 0.8688 0.19809 0.19461 -0.0755 0.0319 1.0000
15.500 0.8709 0.20156 0.19806 -0.0792 0.0316 1.0000
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Polar data table (+)
Polar graphs
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