AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 200,000 Max Cl/Cd: 81.35 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100a-il-200000-n5.txt Download as CSV file: xf-ah79100a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3934 0.08694 0.08335 -0.0425 1.0000 0.0175
-9.000 -0.4020 0.08240 0.07887 -0.0437 1.0000 0.0173
-8.750 -0.4157 0.07770 0.07427 -0.0444 1.0000 0.0171
-8.500 -0.5117 0.04916 0.04567 -0.0674 0.9924 0.0155
-8.250 -0.4928 0.03664 0.03223 -0.0877 0.9815 0.0155
-8.000 -0.4686 0.03158 0.02665 -0.0935 0.9758 0.0159
-7.750 -0.4399 0.02872 0.02345 -0.0969 0.9714 0.0164
-7.500 -0.4078 0.02629 0.02066 -0.1001 0.9685 0.0170
-7.250 -0.3795 0.02421 0.01821 -0.1018 0.9636 0.0179
-7.000 -0.3487 0.02225 0.01589 -0.1035 0.9596 0.0190
-6.750 -0.3153 0.02073 0.01401 -0.1054 0.9568 0.0206
-6.500 -0.2817 0.01963 0.01285 -0.1074 0.9544 0.0225
-6.250 -0.2541 0.01878 0.01185 -0.1078 0.9487 0.0243
-6.000 -0.2226 0.01775 0.01062 -0.1089 0.9445 0.0262
-5.750 -0.1894 0.01683 0.00964 -0.1104 0.9413 0.0288
-5.500 -0.1594 0.01620 0.00894 -0.1111 0.9361 0.0316
-5.250 -0.1290 0.01557 0.00816 -0.1117 0.9304 0.0343
-5.000 -0.0962 0.01477 0.00733 -0.1130 0.9261 0.0380
-4.750 -0.0676 0.01424 0.00673 -0.1133 0.9194 0.0415
-4.500 -0.0371 0.01371 0.00612 -0.1139 0.9138 0.0466
-4.250 -0.0053 0.01322 0.00558 -0.1148 0.9096 0.0544
-4.000 0.0218 0.01281 0.00515 -0.1147 0.9024 0.0643
-3.750 0.0521 0.01240 0.00474 -0.1152 0.8973 0.0814
-3.500 0.0807 0.01198 0.00440 -0.1155 0.8912 0.1128
-3.250 0.1088 0.01149 0.00412 -0.1158 0.8846 0.1709
-3.000 0.1380 0.01101 0.00390 -0.1163 0.8789 0.2522
-2.750 0.1650 0.01077 0.00379 -0.1162 0.8710 0.3084
-2.250 0.2212 0.01049 0.00364 -0.1160 0.8570 0.3955
-2.000 0.2502 0.01040 0.00355 -0.1160 0.8508 0.4253
-1.750 0.2770 0.01035 0.00352 -0.1156 0.8423 0.4497
-1.500 0.3056 0.01029 0.00345 -0.1155 0.8354 0.4748
-1.250 0.3324 0.01025 0.00342 -0.1151 0.8257 0.4927
-1.000 0.3602 0.01021 0.00335 -0.1149 0.8173 0.5094
-0.750 0.3877 0.01018 0.00331 -0.1146 0.8082 0.5251
-0.500 0.4150 0.01016 0.00329 -0.1143 0.7991 0.5392
-0.250 0.4429 0.01013 0.00324 -0.1140 0.7904 0.5547
0.000 0.4697 0.01011 0.00323 -0.1136 0.7794 0.5696
0.250 0.4968 0.01009 0.00321 -0.1132 0.7680 0.5833
0.500 0.5239 0.01007 0.00320 -0.1129 0.7566 0.5975
0.750 0.5510 0.01006 0.00319 -0.1125 0.7454 0.6136
1.000 0.5779 0.01006 0.00322 -0.1121 0.7334 0.6304
1.250 0.6046 0.01006 0.00325 -0.1117 0.7206 0.6481
1.750 0.6570 0.01007 0.00332 -0.1106 0.6916 0.6877
2.000 0.6827 0.01008 0.00338 -0.1099 0.6768 0.7132
2.250 0.7082 0.01008 0.00346 -0.1092 0.6622 0.7462
2.500 0.7332 0.01004 0.00352 -0.1083 0.6467 0.7978
2.750 0.7635 0.00987 0.00351 -0.1084 0.6290 1.0000
3.000 0.7900 0.01006 0.00362 -0.1081 0.6114 1.0000
3.250 0.8164 0.01026 0.00377 -0.1077 0.5946 1.0000
3.500 0.8423 0.01048 0.00393 -0.1073 0.5757 1.0000
3.750 0.8674 0.01075 0.00409 -0.1067 0.5534 1.0000
4.000 0.8924 0.01102 0.00428 -0.1061 0.5298 1.0000
4.250 0.9174 0.01131 0.00451 -0.1055 0.5094 1.0000
4.500 0.9426 0.01159 0.00476 -0.1049 0.4903 1.0000
4.750 0.9672 0.01189 0.00501 -0.1043 0.4682 1.0000
5.000 0.9912 0.01223 0.00531 -0.1036 0.4435 1.0000
5.250 1.0144 0.01262 0.00561 -0.1027 0.4160 1.0000
5.500 1.0369 0.01307 0.00595 -0.1018 0.3843 1.0000
5.750 1.0588 0.01357 0.00633 -0.1008 0.3506 1.0000
6.000 1.0800 0.01412 0.00678 -0.0997 0.3172 1.0000
6.250 1.1011 0.01471 0.00725 -0.0987 0.2829 1.0000
6.500 1.1211 0.01539 0.00778 -0.0975 0.2462 1.0000
6.750 1.1388 0.01628 0.00841 -0.0961 0.1997 1.0000
7.000 1.1557 0.01726 0.00912 -0.0947 0.1536 1.0000
7.250 1.1732 0.01819 0.00988 -0.0933 0.1192 1.0000
7.500 1.1913 0.01905 0.01062 -0.0920 0.0937 1.0000
7.750 1.2089 0.01993 0.01139 -0.0906 0.0721 1.0000
8.000 1.2258 0.02084 0.01222 -0.0891 0.0545 1.0000
8.250 1.2418 0.02180 0.01313 -0.0875 0.0420 1.0000
8.500 1.2570 0.02280 0.01414 -0.0857 0.0328 1.0000
8.750 1.2721 0.02374 0.01513 -0.0839 0.0271 1.0000
9.000 1.2844 0.02478 0.01621 -0.0817 0.0234 1.0000
9.250 1.2967 0.02574 0.01726 -0.0795 0.0212 1.0000
9.500 1.3063 0.02690 0.01848 -0.0771 0.0196 1.0000
9.750 1.3138 0.02821 0.01989 -0.0745 0.0185 1.0000
10.000 1.3224 0.02946 0.02130 -0.0722 0.0177 1.0000
10.250 1.3298 0.03085 0.02281 -0.0699 0.0169 1.0000
10.500 1.3365 0.03234 0.02442 -0.0677 0.0163 1.0000
10.750 1.3429 0.03391 0.02610 -0.0657 0.0157 1.0000
11.000 1.3485 0.03560 0.02789 -0.0639 0.0151 1.0000
11.250 1.3520 0.03755 0.02993 -0.0620 0.0146 1.0000
11.500 1.3523 0.03993 0.03238 -0.0602 0.0140 1.0000
11.750 1.3583 0.04183 0.03445 -0.0588 0.0136 1.0000
12.000 1.3632 0.04392 0.03670 -0.0576 0.0132 1.0000
12.250 1.3663 0.04630 0.03926 -0.0564 0.0128 1.0000
12.500 1.3689 0.04880 0.04192 -0.0553 0.0126 1.0000
12.750 1.3708 0.05146 0.04474 -0.0544 0.0123 1.0000
13.000 1.3718 0.05430 0.04774 -0.0537 0.0120 1.0000
13.250 1.3718 0.05734 0.05095 -0.0532 0.0118 1.0000
13.500 1.3709 0.06060 0.05437 -0.0529 0.0117 1.0000
13.750 1.3686 0.06409 0.05803 -0.0529 0.0115 1.0000
14.000 1.3651 0.06784 0.06196 -0.0532 0.0113 1.0000
14.250 1.3605 0.07187 0.06617 -0.0538 0.0112 1.0000
14.500 1.3546 0.07625 0.07072 -0.0547 0.0111 1.0000
14.750 1.3475 0.08098 0.07563 -0.0559 0.0110 1.0000
15.000 1.3392 0.08610 0.08093 -0.0576 0.0109 1.0000
15.250 1.3298 0.09159 0.08661 -0.0597 0.0108 1.0000
15.500 1.3191 0.09751 0.09271 -0.0623 0.0107 1.0000
15.750 1.3074 0.10390 0.09928 -0.0654 0.0107 1.0000
16.000 1.2947 0.11077 0.10634 -0.0690 0.0106 1.0000
16.250 1.2808 0.11817 0.11393 -0.0732 0.0106 1.0000
16.500 1.2658 0.12615 0.12211 -0.0780 0.0106 1.0000
16.750 1.2492 0.13500 0.13117 -0.0836 0.0106 1.0000
17.000 1.2282 0.14574 0.14214 -0.0906 0.0107 1.0000
17.250 1.1659 0.17125 0.16812 -0.1076 0.0113 1.0000
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