AH 95-160 (ah95160-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 500,000 Max Cl/Cd: 128.07 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah95160-il-500000-n5.txt Download as CSV file: xf-ah95160-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6762 0.04627 0.04188 -0.0980 0.6998 0.0139
-13.000 -0.6961 0.03798 0.03329 -0.1078 0.6980 0.0139
-12.750 -0.7011 0.03431 0.02944 -0.1110 0.6958 0.0140
-12.500 -0.6974 0.03209 0.02707 -0.1118 0.6937 0.0141
-12.250 -0.6857 0.03033 0.02516 -0.1124 0.6914 0.0143
-12.000 -0.6706 0.02885 0.02352 -0.1127 0.6892 0.0144
-11.750 -0.6532 0.02754 0.02207 -0.1130 0.6870 0.0146
-11.500 -0.6340 0.02636 0.02074 -0.1132 0.6850 0.0148
-11.000 -0.5919 0.02426 0.01835 -0.1136 0.6815 0.0154
-10.750 -0.5695 0.02326 0.01721 -0.1138 0.6798 0.0157
-10.500 -0.5463 0.02232 0.01612 -0.1139 0.6781 0.0161
-10.250 -0.5225 0.02143 0.01507 -0.1141 0.6763 0.0164
-10.000 -0.4980 0.02062 0.01411 -0.1143 0.6745 0.0166
-9.750 -0.4738 0.01975 0.01314 -0.1144 0.6726 0.0169
-9.500 -0.4484 0.01907 0.01239 -0.1146 0.6708 0.0172
-9.250 -0.4224 0.01849 0.01172 -0.1148 0.6690 0.0176
-9.000 -0.3961 0.01796 0.01109 -0.1150 0.6673 0.0180
-8.750 -0.3694 0.01744 0.01048 -0.1153 0.6658 0.0184
-8.500 -0.3424 0.01692 0.00988 -0.1155 0.6644 0.0189
-8.250 -0.3151 0.01643 0.00931 -0.1158 0.6629 0.0194
-8.000 -0.2876 0.01596 0.00876 -0.1160 0.6613 0.0199
-7.750 -0.2602 0.01549 0.00826 -0.1163 0.6596 0.0206
-7.500 -0.2323 0.01513 0.00786 -0.1166 0.6578 0.0214
-7.250 -0.2042 0.01478 0.00746 -0.1169 0.6561 0.0222
-7.000 -0.1760 0.01445 0.00704 -0.1172 0.6545 0.0231
-6.750 -0.1479 0.01408 0.00663 -0.1175 0.6530 0.0240
-6.500 -0.1196 0.01378 0.00629 -0.1178 0.6516 0.0250
-6.250 -0.0911 0.01352 0.00597 -0.1181 0.6501 0.0262
-6.000 -0.0625 0.01326 0.00566 -0.1184 0.6487 0.0275
-5.750 -0.0337 0.01299 0.00540 -0.1188 0.6471 0.0292
-5.500 -0.0048 0.01277 0.00515 -0.1192 0.6455 0.0313
-5.250 0.0241 0.01253 0.00493 -0.1196 0.6439 0.0336
-5.000 0.0532 0.01234 0.00471 -0.1200 0.6424 0.0362
-4.750 0.0822 0.01214 0.00452 -0.1204 0.6409 0.0391
-4.500 0.1114 0.01198 0.00433 -0.1208 0.6393 0.0426
-4.250 0.1405 0.01182 0.00418 -0.1212 0.6377 0.0466
-4.000 0.1697 0.01168 0.00402 -0.1216 0.6361 0.0507
-3.750 0.1990 0.01158 0.00389 -0.1220 0.6346 0.0553
-3.500 0.2282 0.01147 0.00378 -0.1224 0.6332 0.0602
-3.250 0.2576 0.01137 0.00368 -0.1228 0.6319 0.0649
-3.000 0.2870 0.01124 0.00359 -0.1233 0.6305 0.0707
-2.750 0.3164 0.01114 0.00350 -0.1237 0.6289 0.0763
-2.500 0.3458 0.01103 0.00342 -0.1242 0.6271 0.0831
-2.250 0.3753 0.01093 0.00333 -0.1246 0.6254 0.0901
-2.000 0.4047 0.01085 0.00326 -0.1251 0.6237 0.0986
-1.750 0.4342 0.01074 0.00319 -0.1256 0.6223 0.1112
-1.500 0.4636 0.01063 0.00313 -0.1261 0.6208 0.1302
-1.250 0.4930 0.01048 0.00308 -0.1266 0.6193 0.1644
-1.000 0.5224 0.01029 0.00304 -0.1272 0.6178 0.2208
-0.750 0.5518 0.01003 0.00303 -0.1279 0.6162 0.3059
-0.500 0.5812 0.00972 0.00305 -0.1287 0.6146 0.4100
-0.250 0.6106 0.00943 0.00310 -0.1294 0.6129 0.5215
0.000 0.6398 0.00928 0.00317 -0.1299 0.6112 0.5971
0.250 0.6689 0.00921 0.00323 -0.1302 0.6093 0.6487
0.500 0.6978 0.00917 0.00328 -0.1306 0.6075 0.6844
0.750 0.7265 0.00913 0.00334 -0.1308 0.6057 0.7220
1.000 0.7536 0.00907 0.00344 -0.1306 0.6042 0.7804
1.250 0.7802 0.00906 0.00354 -0.1303 0.6027 0.8267
1.500 0.8067 0.00910 0.00362 -0.1300 0.6011 0.8529
1.750 0.8337 0.00913 0.00371 -0.1298 0.5992 0.8709
2.000 0.8606 0.00916 0.00379 -0.1297 0.5971 0.8858
2.250 0.8873 0.00920 0.00386 -0.1295 0.5952 0.8996
2.500 0.9137 0.00924 0.00393 -0.1293 0.5932 0.9137
2.750 0.9395 0.00927 0.00398 -0.1289 0.5912 0.9286
3.000 0.9651 0.00929 0.00401 -0.1284 0.5892 0.9448
3.250 0.9927 0.00932 0.00403 -0.1284 0.5873 0.9636
3.500 1.0248 0.00937 0.00407 -0.1296 0.5854 0.9909
3.750 1.0545 0.00946 0.00420 -0.1302 0.5831 0.9998
4.000 1.0837 0.00956 0.00432 -0.1308 0.5807 0.9998
4.250 1.1127 0.00966 0.00444 -0.1313 0.5781 0.9998
4.500 1.1416 0.00975 0.00454 -0.1318 0.5755 0.9998
4.750 1.1704 0.00984 0.00462 -0.1323 0.5727 0.9998
5.000 1.1988 0.00995 0.00472 -0.1327 0.5696 0.9998
5.250 1.2267 0.01004 0.00488 -0.1330 0.5650 0.9998
5.500 1.2544 0.01013 0.00497 -0.1332 0.5595 0.9998
5.750 1.2817 0.01023 0.00506 -0.1334 0.5538 0.9998
6.000 1.3085 0.01034 0.00520 -0.1335 0.5458 0.9998
6.250 1.3346 0.01047 0.00532 -0.1335 0.5376 0.9998
6.500 1.3602 0.01063 0.00549 -0.1334 0.5280 0.9998
6.750 1.3857 0.01082 0.00569 -0.1333 0.5192 0.9998
7.000 1.4098 0.01105 0.00589 -0.1330 0.5098 0.9998
7.250 1.4340 0.01129 0.00615 -0.1327 0.4988 0.9998
7.500 1.4567 0.01158 0.00644 -0.1322 0.4870 0.9998
7.750 1.4773 0.01196 0.00678 -0.1313 0.4729 0.9998
8.000 1.4952 0.01243 0.00721 -0.1300 0.4556 0.9998
8.250 1.5067 0.01311 0.00781 -0.1277 0.4340 0.9998
8.500 1.5111 0.01402 0.00862 -0.1243 0.4087 0.9998
8.750 1.5095 0.01545 0.00992 -0.1207 0.3798 0.9998
9.000 1.5039 0.01741 0.01175 -0.1171 0.3497 0.9998
9.250 1.4971 0.01977 0.01398 -0.1141 0.3214 0.9998
9.500 1.4907 0.02232 0.01642 -0.1114 0.2951 0.9998
9.750 1.4855 0.02489 0.01889 -0.1090 0.2712 0.9998
10.000 1.4806 0.02743 0.02135 -0.1067 0.2497 0.9998
10.250 1.4773 0.02988 0.02372 -0.1046 0.2306 0.9998
10.500 1.4748 0.03224 0.02602 -0.1025 0.2125 0.9998
10.750 1.4730 0.03458 0.02829 -0.1006 0.1956 0.9998
11.000 1.4720 0.03687 0.03053 -0.0988 0.1805 0.9998
11.250 1.4726 0.03910 0.03271 -0.0972 0.1664 0.9998
11.500 1.4741 0.04130 0.03487 -0.0957 0.1535 0.9998
11.750 1.4762 0.04349 0.03701 -0.0943 0.1420 0.9998
12.000 1.4789 0.04566 0.03915 -0.0930 0.1311 0.9998
12.250 1.4837 0.04767 0.04115 -0.0919 0.1217 0.9998
12.500 1.4880 0.04976 0.04323 -0.0908 0.1134 0.9998
12.750 1.4919 0.05188 0.04533 -0.0898 0.1053 0.9998
13.000 1.4978 0.05387 0.04734 -0.0889 0.0989 0.9998
13.250 1.5022 0.05602 0.04947 -0.0879 0.0927 0.9998
13.500 1.5087 0.05798 0.05146 -0.0871 0.0872 0.9998
13.750 1.5124 0.06025 0.05372 -0.0862 0.0818 0.9998
14.000 1.5194 0.06217 0.05568 -0.0855 0.0772 0.9998
14.250 1.5233 0.06446 0.05798 -0.0848 0.0726 0.9998
14.500 1.5291 0.06656 0.06011 -0.0841 0.0687 0.9998
14.750 1.5342 0.06875 0.06232 -0.0834 0.0645 0.9998
15.000 1.5379 0.07113 0.06473 -0.0828 0.0610 0.9998
15.250 1.5434 0.07329 0.06693 -0.0823 0.0575 0.9998
15.500 1.5463 0.07577 0.06943 -0.0817 0.0542 0.9998
15.750 1.5511 0.07808 0.07178 -0.0812 0.0515 0.9998
16.000 1.5554 0.08044 0.07418 -0.0808 0.0487 0.9998
16.250 1.5572 0.08312 0.07689 -0.0804 0.0462 0.9998
16.500 1.5621 0.08546 0.07929 -0.0800 0.0439 0.9998
16.750 1.5647 0.08806 0.08194 -0.0797 0.0417 0.9998
17.000 1.5661 0.09084 0.08475 -0.0794 0.0397 0.9998
17.250 1.5699 0.09333 0.08731 -0.0793 0.0381 0.9998
17.500 1.5718 0.09610 0.09014 -0.0791 0.0363 0.9998
17.750 1.5734 0.09891 0.09300 -0.0791 0.0348 0.9998
18.000 1.5742 0.10186 0.09601 -0.0791 0.0334 0.9998
18.250 1.5769 0.10456 0.09878 -0.0791 0.0322 0.9998
18.500 1.5776 0.10753 0.10182 -0.0793 0.0309 0.9998
18.750 1.5777 0.11060 0.10495 -0.0795 0.0297 0.9998
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Polar data table (+)
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