AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 200,000 Max Cl/Cd: 65.05 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-9-il-200000-n5.txt Download as CSV file: xf-ah21-9-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4979 0.09293 0.08928 -0.0254 1.0000 0.0168
-8.750 -0.5008 0.08931 0.08571 -0.0260 1.0000 0.0160
-8.500 -0.5060 0.08555 0.08201 -0.0268 1.0000 0.0155
-8.250 -0.5145 0.08181 0.07833 -0.0274 1.0000 0.0151
-8.000 -0.5273 0.07838 0.07498 -0.0274 1.0000 0.0146
-7.750 -0.5390 0.07392 0.07057 -0.0294 1.0000 0.0142
-7.500 -0.5471 0.06842 0.06507 -0.0324 1.0000 0.0138
-7.250 -0.5583 0.05872 0.05522 -0.0368 1.0000 0.0126
-7.000 -0.5585 0.05268 0.04899 -0.0375 1.0000 0.0124
-6.750 -0.5549 0.04721 0.04327 -0.0374 1.0000 0.0122
-6.500 -0.5496 0.04206 0.03781 -0.0370 1.0000 0.0123
-6.250 -0.5409 0.03757 0.03297 -0.0365 1.0000 0.0125
-6.000 -0.5278 0.03418 0.02925 -0.0359 1.0000 0.0130
-5.750 -0.5098 0.03253 0.02743 -0.0356 0.9998 0.0139
-5.500 -0.4822 0.03000 0.02453 -0.0369 0.9978 0.0158
-5.250 -0.4542 0.02630 0.02019 -0.0377 0.9959 0.0168
-5.000 -0.4251 0.02339 0.01671 -0.0383 0.9945 0.0175
-4.750 -0.3964 0.02143 0.01429 -0.0386 0.9928 0.0182
-4.500 -0.3684 0.01955 0.01207 -0.0389 0.9911 0.0200
-4.250 -0.3396 0.01837 0.01074 -0.0395 0.9891 0.0217
-4.000 -0.3100 0.01724 0.00944 -0.0399 0.9873 0.0226
-3.750 -0.2799 0.01630 0.00834 -0.0404 0.9855 0.0237
-3.500 -0.2489 0.01554 0.00748 -0.0412 0.9838 0.0250
-3.250 -0.2178 0.01502 0.00688 -0.0421 0.9820 0.0271
-3.000 -0.1900 0.01452 0.00632 -0.0422 0.9788 0.0286
-2.750 -0.1604 0.01389 0.00561 -0.0428 0.9760 0.0301
-2.500 -0.1289 0.01350 0.00513 -0.0436 0.9734 0.0325
-2.250 -0.0960 0.01321 0.00477 -0.0448 0.9711 0.0379
-2.000 -0.0637 0.01279 0.00448 -0.0460 0.9689 0.0712
-1.750 -0.0375 0.01214 0.00430 -0.0461 0.9647 0.1888
-1.500 -0.0098 0.01118 0.00424 -0.0469 0.9615 0.4214
-1.250 0.0108 0.01009 0.00448 -0.0451 0.9585 0.7545
-1.000 0.0390 0.00989 0.00463 -0.0440 0.9564 0.9016
-0.750 0.0883 0.00986 0.00457 -0.0483 0.9561 0.9723
-0.500 0.1229 0.00981 0.00444 -0.0500 0.9511 1.0000
-0.250 0.1562 0.00979 0.00435 -0.0512 0.9465 1.0000
0.000 0.1938 0.00977 0.00427 -0.0533 0.9433 1.0000
0.250 0.2211 0.00972 0.00418 -0.0532 0.9356 1.0000
0.500 0.2587 0.00962 0.00407 -0.0552 0.9310 1.0000
0.750 0.2892 0.00952 0.00396 -0.0556 0.9227 1.0000
1.000 0.3295 0.00931 0.00376 -0.0580 0.9166 1.0000
1.250 0.3605 0.00914 0.00361 -0.0583 0.9051 1.0000
1.500 0.3940 0.00894 0.00343 -0.0592 0.8914 1.0000
1.750 0.4295 0.00873 0.00324 -0.0604 0.8743 1.0000
2.000 0.4644 0.00855 0.00309 -0.0614 0.8496 1.0000
2.250 0.5057 0.00837 0.00288 -0.0636 0.8093 1.0000
2.500 0.5464 0.00840 0.00264 -0.0656 0.7265 1.0000
2.750 0.5676 0.00896 0.00264 -0.0637 0.6097 1.0000
3.000 0.5817 0.00971 0.00288 -0.0608 0.4949 1.0000
3.250 0.5971 0.01048 0.00317 -0.0584 0.3922 1.0000
3.500 0.6140 0.01128 0.00352 -0.0565 0.2920 1.0000
3.750 0.6330 0.01204 0.00389 -0.0551 0.2090 1.0000
4.000 0.6538 0.01272 0.00428 -0.0540 0.1488 1.0000
4.250 0.6753 0.01336 0.00474 -0.0530 0.1049 1.0000
4.500 0.6978 0.01393 0.00518 -0.0522 0.0781 1.0000
4.750 0.7206 0.01447 0.00566 -0.0513 0.0609 1.0000
5.000 0.7433 0.01505 0.00622 -0.0505 0.0503 1.0000
5.250 0.7663 0.01561 0.00684 -0.0496 0.0431 1.0000
5.500 0.7879 0.01637 0.00762 -0.0485 0.0379 1.0000
5.750 0.8110 0.01694 0.00833 -0.0476 0.0336 1.0000
6.000 0.8332 0.01763 0.00908 -0.0467 0.0302 1.0000
6.250 0.8529 0.01883 0.01032 -0.0454 0.0278 1.0000
6.500 0.8752 0.01972 0.01134 -0.0444 0.0267 1.0000
6.750 0.8974 0.02079 0.01257 -0.0434 0.0253 1.0000
7.000 0.9199 0.02201 0.01395 -0.0425 0.0239 1.0000
7.250 0.9422 0.02294 0.01500 -0.0416 0.0219 1.0000
7.500 0.9635 0.02394 0.01614 -0.0408 0.0202 1.0000
7.750 0.9825 0.02650 0.01895 -0.0396 0.0187 1.0000
8.000 1.0036 0.02763 0.02037 -0.0385 0.0175 1.0000
8.250 1.0234 0.02889 0.02191 -0.0373 0.0157 1.0000
8.500 1.0408 0.03063 0.02394 -0.0358 0.0145 1.0000
8.750 1.0567 0.03230 0.02586 -0.0343 0.0136 1.0000
9.000 1.0697 0.03423 0.02800 -0.0326 0.0129 1.0000
9.250 1.0732 0.03795 0.03216 -0.0298 0.0122 1.0000
9.500 1.0770 0.04116 0.03590 -0.0269 0.0116 1.0000
9.750 1.0739 0.04502 0.04027 -0.0236 0.0107 1.0000
10.000 1.0629 0.04929 0.04496 -0.0200 0.0102 1.0000
10.250 1.0456 0.05315 0.04913 -0.0160 0.0099 1.0000
10.500 1.0227 0.05753 0.05377 -0.0128 0.0099 1.0000
10.750 0.9962 0.06273 0.05920 -0.0114 0.0100 1.0000
11.000 0.9672 0.06922 0.06588 -0.0129 0.0103 1.0000
11.250 0.9400 0.07749 0.07429 -0.0182 0.0108 1.0000
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Polar data table (+)
Polar graphs
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