AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 83-150 Q (ah83150q-il) Reynolds number: 200,000 Max Cl/Cd: 73.87 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah83150q-il-200000.txt Download as CSV file: xf-ah83150q-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-150 Q
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2199 0.09853 0.09454 -0.0673 0.7972 0.0391
-9.750 -0.2331 0.09344 0.08949 -0.0743 0.7943 0.0395
-9.500 -0.2348 0.08869 0.08477 -0.0786 0.7909 0.0395
-9.250 -0.2100 0.08699 0.08306 -0.0718 0.7886 0.0410
-9.000 -0.1992 0.08485 0.08092 -0.0714 0.7858 0.0431
-8.750 -0.1977 0.08144 0.07751 -0.0735 0.7833 0.0445
-8.500 -0.2020 0.07717 0.07324 -0.0770 0.7809 0.0459
-8.250 -0.2087 0.07269 0.06878 -0.0813 0.7779 0.0463
-8.000 -0.2254 0.06860 0.06468 -0.0841 0.7741 0.0473
-7.750 -0.2424 0.06567 0.06157 -0.0851 0.7707 0.0483
-7.500 -0.2584 0.06423 0.05969 -0.0844 0.7679 0.0490
-7.250 -0.2517 0.05800 0.05355 -0.0849 0.7660 0.0502
-7.000 -0.2378 0.05543 0.05101 -0.0848 0.7639 0.0514
-6.750 -0.2260 0.05313 0.04870 -0.0848 0.7609 0.0532
-6.500 -0.2154 0.05075 0.04618 -0.0845 0.7578 0.0560
-6.250 -0.2139 0.04845 0.04323 -0.0831 0.7548 0.0614
-6.000 -0.1961 0.04507 0.03998 -0.0833 0.7526 0.0633
-5.750 -0.1789 0.04311 0.03795 -0.0829 0.7505 0.0664
-5.500 -0.1661 0.04147 0.03575 -0.0816 0.7484 0.0750
-5.250 -0.1458 0.03893 0.03336 -0.0820 0.7452 0.0780
-5.000 -0.1281 0.03772 0.03175 -0.0812 0.7420 0.0893
-4.750 -0.1066 0.03550 0.02963 -0.0813 0.7395 0.0940
-4.500 -0.0866 0.03392 0.02786 -0.0808 0.7372 0.1070
-4.250 -0.0655 0.03247 0.02626 -0.0804 0.7351 0.1222
-4.000 -0.0228 0.02642 0.01870 -0.0761 0.7335 0.0374
-3.750 0.0051 0.02524 0.01708 -0.0752 0.7304 0.0319
-3.500 0.0315 0.02377 0.01559 -0.0750 0.7273 0.0309
-3.250 0.0579 0.02274 0.01449 -0.0746 0.7246 0.0303
-3.000 0.0839 0.02189 0.01360 -0.0741 0.7221 0.0303
-2.750 0.1094 0.02118 0.01282 -0.0734 0.7199 0.0311
-2.500 0.1332 0.02044 0.01211 -0.0727 0.7180 0.0339
-2.250 0.1565 0.02025 0.01197 -0.0723 0.7149 0.0377
-2.000 0.1795 0.02008 0.01179 -0.0720 0.7109 0.0399
-1.750 0.2038 0.01972 0.01139 -0.0715 0.7078 0.0470
-1.500 0.2155 0.01736 0.01085 -0.0700 0.7053 0.4882
-1.250 0.2139 0.01829 0.01282 -0.0605 0.7032 0.8280
-1.000 0.2166 0.01920 0.01373 -0.0520 0.7014 0.8753
-0.750 0.3283 0.01980 0.01415 -0.0623 0.6995 0.9408
-0.500 0.3628 0.01999 0.01428 -0.0643 0.6949 0.9483
-0.250 0.4072 0.01992 0.01409 -0.0678 0.6919 0.9551
0.000 0.4364 0.01983 0.01389 -0.0683 0.6894 0.9605
0.250 0.4735 0.01962 0.01357 -0.0703 0.6873 0.9631
0.500 0.5066 0.01953 0.01336 -0.0716 0.6854 0.9661
0.750 0.5261 0.02009 0.01399 -0.0715 0.6789 0.9704
1.000 0.5517 0.02008 0.01394 -0.0715 0.6754 0.9732
1.250 0.5856 0.01988 0.01367 -0.0729 0.6730 0.9750
1.500 0.6172 0.01971 0.01341 -0.0738 0.6709 0.9768
1.750 0.6404 0.02013 0.01388 -0.0740 0.6655 0.9793
2.000 0.6636 0.02029 0.01405 -0.0739 0.6609 0.9814
2.250 0.6902 0.02014 0.01386 -0.0738 0.6580 0.9832
2.500 0.7177 0.01993 0.01359 -0.0738 0.6557 0.9846
2.750 0.7432 0.02018 0.01387 -0.0742 0.6509 0.9860
3.000 0.7695 0.02035 0.01408 -0.0747 0.6454 0.9878
3.250 0.7990 0.02009 0.01380 -0.0751 0.6424 0.9890
3.500 0.8285 0.01977 0.01344 -0.0754 0.6400 0.9900
3.750 0.8496 0.02016 0.01391 -0.0751 0.6340 0.9920
4.000 0.8752 0.02015 0.01394 -0.0751 0.6293 0.9936
4.250 0.9041 0.01982 0.01360 -0.0753 0.6263 0.9945
4.500 0.9360 0.01940 0.01313 -0.0759 0.6239 0.9952
4.750 0.9558 0.01988 0.01375 -0.0756 0.6163 0.9972
5.000 0.9865 0.01957 0.01346 -0.0762 0.6123 0.9986
5.250 1.0192 0.01907 0.01294 -0.0769 0.6095 0.9995
5.500 1.0336 0.01938 0.01336 -0.0752 0.6023 1.0000
5.750 1.0560 0.01911 0.01313 -0.0742 0.5975 1.0000
6.000 1.0862 0.01846 0.01245 -0.0742 0.5941 1.0000
6.250 1.0963 0.01853 0.01264 -0.0714 0.5850 1.0000
6.500 1.1272 0.01766 0.01172 -0.0713 0.5795 1.0000
6.750 1.1373 0.01771 0.01188 -0.0685 0.5705 1.0000
7.000 1.1627 0.01726 0.01142 -0.0679 0.5651 1.0000
7.250 1.1708 0.01740 0.01168 -0.0647 0.5566 1.0000
7.500 1.1938 0.01703 0.01132 -0.0637 0.5501 1.0000
7.750 1.1979 0.01718 0.01158 -0.0599 0.5408 1.0000
8.000 1.2164 0.01693 0.01134 -0.0581 0.5329 1.0000
8.250 1.2232 0.01700 0.01148 -0.0548 0.5227 1.0000
8.500 1.2375 0.01707 0.01163 -0.0528 0.5114 1.0000
8.750 1.2560 0.01712 0.01172 -0.0516 0.4988 1.0000
9.000 1.2750 0.01726 0.01188 -0.0506 0.4852 1.0000
9.250 1.2919 0.01751 0.01216 -0.0494 0.4698 1.0000
9.500 1.3045 0.01788 0.01253 -0.0476 0.4524 1.0000
9.750 1.3137 0.01843 0.01301 -0.0455 0.4328 1.0000
10.000 1.3193 0.01928 0.01382 -0.0433 0.4116 1.0000
10.250 1.3233 0.02039 0.01485 -0.0412 0.3898 1.0000
10.500 1.3269 0.02167 0.01606 -0.0394 0.3692 1.0000
10.750 1.3292 0.02316 0.01753 -0.0378 0.3483 1.0000
11.000 1.3301 0.02483 0.01912 -0.0361 0.3276 1.0000
11.250 1.3304 0.02663 0.02087 -0.0346 0.3072 1.0000
11.500 1.3297 0.02859 0.02277 -0.0332 0.2865 1.0000
11.750 1.3277 0.03071 0.02480 -0.0318 0.2668 1.0000
12.000 1.3262 0.03287 0.02691 -0.0305 0.2470 1.0000
12.250 1.3249 0.03509 0.02907 -0.0294 0.2287 1.0000
12.500 1.3236 0.03736 0.03129 -0.0283 0.2121 1.0000
12.750 1.3232 0.03967 0.03356 -0.0274 0.1971 1.0000
13.000 1.3236 0.04198 0.03584 -0.0266 0.1834 1.0000
13.250 1.3246 0.04434 0.03818 -0.0260 0.1707 1.0000
13.500 1.3255 0.04676 0.04058 -0.0255 0.1590 1.0000
13.750 1.3258 0.04931 0.04310 -0.0250 0.1480 1.0000
14.000 1.3250 0.05205 0.04580 -0.0247 0.1374 1.0000
14.250 1.3263 0.05469 0.04848 -0.0245 0.1265 1.0000
14.500 1.3267 0.05746 0.05129 -0.0243 0.1162 1.0000
14.750 1.3253 0.06047 0.05426 -0.0241 0.1071 1.0000
15.000 1.3249 0.06347 0.05727 -0.0242 0.0990 1.0000
15.250 1.3267 0.06628 0.06016 -0.0242 0.0914 1.0000
15.500 1.3266 0.06926 0.06306 -0.0242 0.0855 1.0000
15.750 1.3306 0.07195 0.06589 -0.0245 0.0803 1.0000
16.000 1.3309 0.07511 0.06906 -0.0250 0.0753 1.0000
16.250 1.3344 0.07781 0.07182 -0.0252 0.0712 1.0000
16.500 1.3367 0.08085 0.07498 -0.0258 0.0674 1.0000
16.750 1.3377 0.08395 0.07807 -0.0264 0.0638 1.0000
17.000 1.3401 0.08697 0.08120 -0.0270 0.0606 1.0000
17.250 1.3411 0.09034 0.08472 -0.0280 0.0575 1.0000
17.500 1.3413 0.09379 0.08823 -0.0290 0.0547 1.0000
17.750 1.3430 0.09684 0.09129 -0.0297 0.0518 1.0000
18.000 1.3426 0.10058 0.09523 -0.0310 0.0495 1.0000
18.250 1.3419 0.10437 0.09914 -0.0324 0.0471 1.0000
18.500 1.3406 0.10816 0.10297 -0.0339 0.0447 1.0000
18.750 1.3399 0.11183 0.10673 -0.0351 0.0423 1.0000
19.000 1.3367 0.11621 0.11131 -0.0370 0.0401 1.0000
19.250 1.3322 0.12081 0.11602 -0.0392 0.0376 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 83-150 Q (ah83150q-il)