AH 95-160 (ah95160-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 100,000 Max Cl/Cd: 24.79 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah95160-il-100000-n5.txt Download as CSV file: xf-ah95160-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 95-160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1779 0.12972 0.12386 -0.0641 0.7822 0.0587
-11.750 -0.1715 0.12649 0.12062 -0.0657 0.7793 0.0591
-11.250 -0.1778 0.11519 0.10926 -0.0723 0.7747 0.0420
-11.000 -0.1676 0.11241 0.10644 -0.0726 0.7721 0.0413
-10.750 -0.1618 0.10908 0.10308 -0.0738 0.7699 0.0406
-10.500 -0.1575 0.10534 0.09937 -0.0759 0.7672 0.0404
-10.250 -0.1544 0.10143 0.09547 -0.0783 0.7645 0.0407
-10.000 -0.1521 0.09739 0.09144 -0.0808 0.7620 0.0409
-9.750 -0.1501 0.09330 0.08736 -0.0833 0.7597 0.0409
-9.250 -0.1475 0.08488 0.07893 -0.0885 0.7553 0.0404
-9.000 -0.1485 0.08015 0.07419 -0.0917 0.7532 0.0401
-8.750 -0.1515 0.07465 0.06872 -0.0962 0.7508 0.0398
-8.500 -0.1618 0.06734 0.06146 -0.1037 0.7477 0.0393
-8.250 -0.1848 0.05668 0.05059 -0.1148 0.7446 0.0387
-8.000 -0.1945 0.04957 0.04309 -0.1192 0.7418 0.0387
-7.750 -0.1910 0.04486 0.03794 -0.1212 0.7395 0.0396
-7.500 -0.1839 0.04009 0.03251 -0.1225 0.7374 0.0412
-7.250 -0.1688 0.03681 0.02865 -0.1230 0.7356 0.0426
-7.000 -0.1472 0.03554 0.02724 -0.1232 0.7332 0.0437
-6.750 -0.1260 0.03397 0.02541 -0.1234 0.7301 0.0450
-6.500 -0.1040 0.03218 0.02323 -0.1236 0.7271 0.0471
-6.250 -0.0805 0.03087 0.02162 -0.1236 0.7246 0.0495
-6.000 -0.0555 0.03015 0.02078 -0.1237 0.7224 0.0518
-5.750 -0.0301 0.02895 0.01928 -0.1237 0.7206 0.0546
-5.500 -0.0042 0.02813 0.01830 -0.1238 0.7188 0.0576
-5.250 0.0221 0.02755 0.01759 -0.1238 0.7170 0.0614
-5.000 0.0461 0.02695 0.01685 -0.1237 0.7136 0.0652
-4.750 0.0707 0.02664 0.01657 -0.1237 0.7106 0.0694
-4.500 0.0963 0.02618 0.01595 -0.1236 0.7081 0.0747
-4.250 0.1218 0.02580 0.01562 -0.1236 0.7060 0.0801
-4.000 0.1484 0.02539 0.01509 -0.1236 0.7040 0.0867
-3.750 0.1750 0.02499 0.01470 -0.1236 0.7022 0.0938
-3.500 0.2022 0.02458 0.01424 -0.1236 0.7006 0.1018
-3.250 0.2255 0.02457 0.01425 -0.1235 0.6974 0.1103
-3.000 0.2482 0.02458 0.01433 -0.1232 0.6942 0.1195
-2.750 0.2726 0.02455 0.01431 -0.1231 0.6915 0.1309
-2.500 0.2981 0.02444 0.01422 -0.1231 0.6891 0.1455
-2.250 0.3247 0.02421 0.01407 -0.1232 0.6870 0.1666
-2.000 0.3520 0.02388 0.01389 -0.1234 0.6852 0.2056
-1.750 0.3792 0.02334 0.01375 -0.1238 0.6837 0.3083
-1.500 0.3985 0.02314 0.01429 -0.1231 0.6808 0.4905
-1.250 0.4136 0.02354 0.01516 -0.1213 0.6766 0.6248
-1.000 0.4318 0.02381 0.01562 -0.1194 0.6735 0.7065
-0.750 0.4512 0.02397 0.01587 -0.1174 0.6710 0.7666
-0.500 0.4713 0.02407 0.01599 -0.1153 0.6691 0.8169
-0.250 0.4915 0.02414 0.01604 -0.1132 0.6675 0.8637
0.000 0.5134 0.02411 0.01601 -0.1111 0.6663 0.9290
0.250 0.5351 0.02546 0.01744 -0.1122 0.6594 0.9998
0.500 0.5569 0.02600 0.01787 -0.1122 0.6560 0.9998
0.750 0.5829 0.02635 0.01810 -0.1125 0.6537 0.9998
1.000 0.6108 0.02662 0.01824 -0.1129 0.6520 0.9998
1.250 0.6405 0.02678 0.01829 -0.1135 0.6506 0.9998
1.500 0.6692 0.02700 0.01841 -0.1140 0.6490 0.9998
2.000 0.6868 0.02998 0.02139 -0.1114 0.6368 0.9998
2.250 0.7157 0.03016 0.02149 -0.1118 0.6352 0.9998
2.500 0.7463 0.03022 0.02148 -0.1123 0.6339 0.9998
3.500 0.8145 0.03398 0.02519 -0.1095 0.6177 0.9998
4.000 0.8189 0.03815 0.02940 -0.1063 0.6030 0.9998
4.250 0.8400 0.03887 0.03011 -0.1060 0.6000 0.9998
4.750 0.8598 0.04193 0.03320 -0.1040 0.5878 0.9998
5.000 0.8897 0.04188 0.03315 -0.1041 0.5864 0.9998
6.000 0.9232 0.04833 0.03972 -0.0996 0.5595 0.9998
6.250 0.9512 0.04831 0.03973 -0.0996 0.5574 0.9998
6.500 0.9818 0.04803 0.03948 -0.0996 0.5559 0.9998
7.000 1.0020 0.05078 0.04234 -0.0975 0.5420 0.9998
7.250 1.0334 0.05031 0.04192 -0.0975 0.5405 0.9998
7.750 1.0559 0.05273 0.04445 -0.0955 0.5263 0.9998
8.250 1.0816 0.05478 0.04664 -0.0936 0.5122 0.9998
8.500 1.1147 0.05380 0.04573 -0.0934 0.5103 0.9998
9.000 1.1437 0.05523 0.04732 -0.0915 0.4957 0.9998
9.500 1.1751 0.05626 0.04851 -0.0896 0.4807 0.9998
10.000 1.2101 0.05678 0.04920 -0.0878 0.4650 0.9998
10.500 1.2205 0.06010 0.05269 -0.0853 0.4407 0.9998
11.000 1.2571 0.06057 0.05333 -0.0837 0.4211 0.9998
11.250 1.2688 0.06164 0.05448 -0.0828 0.4080 0.9998
11.500 1.2860 0.06207 0.05497 -0.0820 0.3951 0.9998
11.750 1.3058 0.06215 0.05509 -0.0812 0.3812 0.9998
12.000 1.3249 0.06230 0.05524 -0.0803 0.3650 0.9998
12.250 1.3440 0.06240 0.05530 -0.0794 0.3464 0.9998
12.500 1.3625 0.06249 0.05527 -0.0783 0.3256 0.9998
12.750 1.3701 0.06400 0.05671 -0.0772 0.3035 0.9998
13.000 1.3766 0.06561 0.05820 -0.0761 0.2814 0.9998
13.250 1.3800 0.06769 0.06017 -0.0750 0.2608 0.9998
13.500 1.3811 0.07013 0.06254 -0.0740 0.2411 0.9998
13.750 1.3815 0.07269 0.06503 -0.0731 0.2230 0.9998
14.000 1.3818 0.07534 0.06761 -0.0722 0.2066 0.9998
14.250 1.3818 0.07809 0.07031 -0.0715 0.1916 0.9998
14.500 1.3824 0.08083 0.07302 -0.0709 0.1781 0.9998
14.750 1.3829 0.08360 0.07578 -0.0704 0.1661 0.9998
15.000 1.3835 0.08640 0.07856 -0.0699 0.1554 0.9998
15.250 1.3840 0.08923 0.08138 -0.0695 0.1455 0.9998
15.500 1.3860 0.09196 0.08416 -0.0692 0.1364 0.9998
15.750 1.3872 0.09476 0.08695 -0.0690 0.1286 0.9998
16.000 1.3888 0.09757 0.08981 -0.0688 0.1211 0.9998
16.250 1.3907 0.10033 0.09260 -0.0687 0.1145 0.9998
16.500 1.3923 0.10318 0.09551 -0.0687 0.1082 0.9998
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