AH 94-156 (ah94156-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 94-156 (ah94156-il) Reynolds number: 200,000 Max Cl/Cd: 72.84 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah94156-il-200000.txt Download as CSV file: xf-ah94156-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-156
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1969 0.10835 0.10464 -0.0960 0.9078 0.0472
-11.750 -0.1813 0.10594 0.10220 -0.0952 0.9039 0.0483
-11.500 -0.1723 0.10330 0.09952 -0.0956 0.9000 0.0495
-11.250 -0.1669 0.10035 0.09656 -0.0966 0.8964 0.0514
-11.000 -0.1664 0.09687 0.09308 -0.0984 0.8920 0.0539
-10.750 -0.1739 0.09272 0.08895 -0.1019 0.8873 0.0561
-10.500 -0.1914 0.08739 0.08364 -0.1076 0.8829 0.0571
-10.000 -0.1874 0.07965 0.07595 -0.1086 0.8764 0.0598
-9.750 -0.1790 0.07759 0.07388 -0.1083 0.8730 0.0614
-9.500 -0.1823 0.07395 0.07024 -0.1101 0.8693 0.0632
-9.250 -0.1991 0.06856 0.06485 -0.1145 0.8650 0.0632
-9.000 -0.2162 0.06461 0.06087 -0.1161 0.8604 0.0642
-8.750 -0.2390 0.06148 0.05765 -0.1153 0.8558 0.0663
-8.500 -0.2591 0.05917 0.05520 -0.1127 0.8522 0.0669
-8.250 -0.2989 0.05985 0.05532 -0.1077 0.8456 0.0700
-7.750 -0.2811 0.05101 0.04661 -0.1074 0.8404 0.0738
-7.500 -0.2735 0.04903 0.04452 -0.1059 0.8380 0.0761
-7.000 -0.2919 0.03806 0.03184 -0.0961 0.8292 0.0471
-6.750 -0.2745 0.03449 0.02819 -0.0951 0.8267 0.0427
-6.500 -0.2628 0.03064 0.02353 -0.0920 0.8243 0.0387
-6.250 -0.2416 0.02904 0.02168 -0.0909 0.8225 0.0391
-6.000 -0.2224 0.02847 0.02110 -0.0902 0.8186 0.0414
-5.750 -0.2018 0.02725 0.01966 -0.0891 0.8149 0.0421
-5.500 -0.1780 0.02604 0.01824 -0.0884 0.8123 0.0428
-5.250 -0.1521 0.02497 0.01700 -0.0879 0.8101 0.0441
-5.000 -0.1255 0.02427 0.01613 -0.0873 0.8083 0.0462
-4.750 -0.1004 0.02297 0.01487 -0.0869 0.8066 0.0499
-4.500 -0.0874 0.02301 0.01495 -0.0852 0.8011 0.0530
-4.250 -0.0671 0.02264 0.01452 -0.0840 0.7976 0.0568
-4.000 -0.0471 0.02190 0.01384 -0.0828 0.7950 0.0638
-3.750 -0.0251 0.02131 0.01325 -0.0817 0.7932 0.0744
-3.500 -0.0030 0.02070 0.01270 -0.0807 0.7916 0.0987
-3.250 -0.0046 0.02078 0.01323 -0.0769 0.7838 0.1616
-3.000 -0.0017 0.01931 0.01303 -0.0734 0.7802 0.4345
-2.750 0.0058 0.01875 0.01382 -0.0675 0.7781 0.7223
-2.500 0.0289 0.01960 0.01464 -0.0646 0.7767 0.8113
-2.250 0.0214 0.02100 0.01604 -0.0588 0.7677 0.8339
-2.000 0.0383 0.02160 0.01655 -0.0555 0.7647 0.8590
-1.750 0.0654 0.02206 0.01691 -0.0532 0.7631 0.8784
-1.500 0.0996 0.02238 0.01711 -0.0525 0.7620 0.8999
-1.250 0.1698 0.02261 0.01718 -0.0589 0.7618 0.9167
-1.000 0.2730 0.02255 0.01692 -0.0727 0.7621 0.9261
-0.750 0.3398 0.02224 0.01646 -0.0800 0.7614 0.9341
-0.500 0.3646 0.02283 0.01705 -0.0806 0.7546 0.9449
-0.250 0.4114 0.02264 0.01677 -0.0846 0.7517 0.9516
0.000 0.4508 0.02231 0.01637 -0.0869 0.7494 0.9581
0.250 0.4982 0.02186 0.01583 -0.0908 0.7478 0.9626
0.500 0.5325 0.02155 0.01545 -0.0921 0.7461 0.9686
0.750 0.5631 0.02193 0.01586 -0.0941 0.7391 0.9739
1.000 0.5991 0.02168 0.01558 -0.0961 0.7357 0.9786
1.250 0.6328 0.02133 0.01519 -0.0974 0.7334 0.9829
1.500 0.6755 0.02078 0.01458 -0.1004 0.7315 0.9858
1.750 0.7035 0.02105 0.01489 -0.1016 0.7253 0.9903
2.000 0.7341 0.02091 0.01476 -0.1026 0.7210 0.9938
2.250 0.7727 0.02041 0.01423 -0.1049 0.7185 0.9963
2.500 0.8110 0.01987 0.01368 -0.1070 0.7164 0.9990
2.750 0.8267 0.02032 0.01420 -0.1058 0.7092 1.0000
3.000 0.8487 0.02015 0.01403 -0.1048 0.7050 1.0000
3.250 0.8755 0.01972 0.01359 -0.1045 0.7023 1.0000
3.500 0.9028 0.01932 0.01318 -0.1043 0.6997 1.0000
3.750 0.9105 0.01980 0.01376 -0.1014 0.6908 1.0000
4.000 0.9384 0.01933 0.01328 -0.1012 0.6877 1.0000
4.250 0.9692 0.01876 0.01271 -0.1015 0.6854 1.0000
4.500 0.9753 0.01923 0.01328 -0.0982 0.6760 1.0000
4.750 1.0052 0.01864 0.01270 -0.0983 0.6725 1.0000
5.000 1.0206 0.01869 0.01281 -0.0963 0.6655 1.0000
5.250 1.0435 0.01837 0.01254 -0.0954 0.6598 1.0000
5.500 1.0764 0.01772 0.01187 -0.0960 0.6562 1.0000
5.750 1.0846 0.01792 0.01218 -0.0927 0.6466 1.0000
6.000 1.1163 0.01731 0.01157 -0.0931 0.6419 1.0000
6.250 1.1253 0.01746 0.01184 -0.0899 0.6323 1.0000
6.500 1.1572 0.01688 0.01125 -0.0904 0.6267 1.0000
6.750 1.1641 0.01701 0.01149 -0.0868 0.6159 1.0000
7.000 1.1798 0.01691 0.01144 -0.0846 0.6066 1.0000
7.250 1.2037 0.01660 0.01115 -0.0837 0.5977 1.0000
7.500 1.2092 0.01672 0.01135 -0.0798 0.5858 1.0000
7.750 1.2172 0.01678 0.01145 -0.0762 0.5739 1.0000
8.000 1.2237 0.01680 0.01148 -0.0723 0.5606 1.0000
8.250 1.2251 0.01686 0.01155 -0.0675 0.5461 1.0000
8.500 1.2197 0.01696 0.01162 -0.0615 0.5319 1.0000
8.750 1.2071 0.01705 0.01168 -0.0542 0.5190 1.0000
9.000 1.1974 0.01722 0.01181 -0.0477 0.5051 1.0000
9.250 1.1959 0.01759 0.01215 -0.0431 0.4891 1.0000
9.500 1.2001 0.01811 0.01264 -0.0399 0.4712 1.0000
9.750 1.2067 0.01876 0.01324 -0.0373 0.4526 1.0000
10.000 1.2142 0.01949 0.01390 -0.0349 0.4336 1.0000
10.250 1.2179 0.02045 0.01487 -0.0324 0.4138 1.0000
10.500 1.2220 0.02150 0.01589 -0.0301 0.3933 1.0000
10.750 1.2255 0.02266 0.01697 -0.0278 0.3727 1.0000
11.000 1.2276 0.02398 0.01827 -0.0256 0.3505 1.0000
11.250 1.2289 0.02541 0.01964 -0.0235 0.3287 1.0000
11.500 1.2298 0.02697 0.02116 -0.0214 0.3050 1.0000
11.750 1.2278 0.02876 0.02286 -0.0193 0.2794 1.0000
12.250 1.2211 0.03291 0.02680 -0.0154 0.2258 1.0000
12.750 1.2098 0.03798 0.03157 -0.0120 0.1653 1.0000
13.000 1.2012 0.04097 0.03437 -0.0104 0.1323 1.0000
13.250 1.1910 0.04427 0.03745 -0.0090 0.1025 1.0000
13.500 1.1817 0.04764 0.04067 -0.0078 0.0802 1.0000
13.750 1.1738 0.05106 0.04399 -0.0069 0.0662 1.0000
14.000 1.1676 0.05443 0.04734 -0.0062 0.0559 1.0000
14.250 1.1634 0.05771 0.05065 -0.0057 0.0490 1.0000
14.500 1.1566 0.06136 0.05428 -0.0053 0.0439 1.0000
14.750 1.1573 0.06429 0.05731 -0.0051 0.0397 1.0000
15.000 1.1566 0.06742 0.06050 -0.0051 0.0369 1.0000
15.250 1.1529 0.07079 0.06386 -0.0048 0.0343 1.0000
15.500 1.1578 0.07336 0.06656 -0.0048 0.0324 1.0000
15.750 1.1620 0.07601 0.06929 -0.0050 0.0305 1.0000
16.000 1.1649 0.07876 0.07204 -0.0051 0.0286 1.0000
16.250 1.1714 0.08090 0.07420 -0.0047 0.0269 1.0000
16.500 1.1786 0.08326 0.07670 -0.0048 0.0257 1.0000
16.750 1.1882 0.08524 0.07879 -0.0046 0.0249 1.0000
17.000 1.1951 0.08766 0.08130 -0.0048 0.0238 1.0000
17.250 1.2034 0.08985 0.08358 -0.0048 0.0230 1.0000
17.500 1.2146 0.09165 0.08541 -0.0046 0.0222 1.0000
17.750 1.2256 0.09377 0.08766 -0.0040 0.0214 1.0000
18.000 1.2265 0.09727 0.09138 -0.0047 0.0212 1.0000
18.250 1.2211 0.10163 0.09596 -0.0062 0.0208 1.0000
18.500 1.2139 0.10635 0.10093 -0.0079 0.0202 1.0000
18.750 1.2078 0.11104 0.10583 -0.0096 0.0199 1.0000
19.000 1.2004 0.11607 0.11109 -0.0115 0.0199 1.0000
19.250 1.1896 0.12177 0.11702 -0.0140 0.0197 1.0000
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Polar data table (+)
Polar graphs
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