AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 200,000 Max Cl/Cd: 62.5 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah81k144-il-200000.txt Download as CSV file: xf-ah81k144-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-K-144/17
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 -0.1278 0.10987 0.10549 -0.1097 0.8378 0.0503
-11.750 -0.1340 0.10646 0.10213 -0.1140 0.8364 0.0511
-11.500 -0.1336 0.10301 0.09870 -0.1168 0.8351 0.0512
-11.250 -0.1233 0.09798 0.09367 -0.1161 0.8341 0.0526
-11.000 -0.1115 0.09542 0.09109 -0.1163 0.8329 0.0534
-10.750 -0.0978 0.09349 0.08914 -0.1163 0.8317 0.0563
-10.500 -0.0959 0.09053 0.08620 -0.1178 0.8303 0.0596
-10.250 -0.1037 0.08682 0.08256 -0.1209 0.8286 0.0619
-10.000 -0.0671 0.07108 0.06725 -0.1118 0.8219 0.0652
-9.750 -0.0570 0.06864 0.06479 -0.1110 0.8205 0.0669
-9.500 -0.0553 0.06568 0.06184 -0.1115 0.8191 0.0682
-9.250 -0.0576 0.06235 0.05853 -0.1122 0.8177 0.0700
-9.000 -0.1160 0.06960 0.06557 -0.1269 0.8207 0.0681
-8.750 -0.1297 0.06554 0.06155 -0.1294 0.8187 0.0685
-8.500 -0.1487 0.06228 0.05828 -0.1294 0.8165 0.0699
-8.250 -0.1695 0.06000 0.05601 -0.1273 0.8144 0.0703
-8.000 -0.1852 0.05734 0.05329 -0.1258 0.8123 0.0722
-7.500 -0.2531 0.04160 0.03622 -0.1170 0.8071 0.0400
-7.250 -0.2514 0.03791 0.03225 -0.1144 0.8052 0.0381
-7.000 -0.2467 0.03458 0.02844 -0.1116 0.8037 0.0361
-6.750 -0.2378 0.03169 0.02498 -0.1088 0.8023 0.0349
-6.500 -0.2251 0.03018 0.02320 -0.1069 0.8000 0.0351
-6.250 -0.2092 0.02895 0.02174 -0.1053 0.7974 0.0358
-6.000 -0.1906 0.02804 0.02063 -0.1040 0.7951 0.0372
-5.750 -0.1705 0.02747 0.01986 -0.1029 0.7933 0.0395
-5.500 -0.1490 0.02644 0.01861 -0.1018 0.7916 0.0414
-5.250 -0.1268 0.02530 0.01747 -0.1010 0.7901 0.0445
-5.000 -0.1028 0.02473 0.01681 -0.1002 0.7887 0.0485
-4.750 -0.0942 0.02469 0.01677 -0.0977 0.7851 0.0528
-4.500 -0.0827 0.02470 0.01683 -0.0956 0.7819 0.0601
-4.250 -0.0668 0.02433 0.01647 -0.0938 0.7792 0.0702
-4.000 -0.0460 0.02399 0.01613 -0.0926 0.7772 0.0898
-3.750 -0.0247 0.02357 0.01583 -0.0916 0.7756 0.1166
-3.500 -0.0016 0.02322 0.01564 -0.0908 0.7743 0.1561
-3.250 -0.0165 0.02430 0.01683 -0.0850 0.7671 0.1698
-3.000 -0.0033 0.02421 0.01697 -0.0829 0.7642 0.2230
-2.750 0.0157 0.02369 0.01685 -0.0815 0.7621 0.3215
-2.500 0.0315 0.02282 0.01672 -0.0792 0.7605 0.4995
-2.250 0.0024 0.02418 0.01824 -0.0708 0.7519 0.5322
-2.000 0.0095 0.02389 0.01885 -0.0658 0.7489 0.7461
-1.750 0.0307 0.02413 0.01910 -0.0633 0.7471 0.8346
-1.500 0.0575 0.02429 0.01921 -0.0618 0.7459 0.8744
-1.250 0.0215 0.02564 0.02061 -0.0521 0.7357 0.8897
-1.000 0.0532 0.02577 0.02068 -0.0521 0.7337 0.9229
-0.750 0.1231 0.02594 0.02072 -0.0596 0.7332 0.9510
-0.500 0.2142 0.02626 0.02085 -0.0713 0.7333 0.9649
-0.250 0.2971 0.02644 0.02089 -0.0817 0.7331 0.9714
0.000 0.3681 0.02647 0.02079 -0.0898 0.7326 0.9794
0.250 0.4517 0.02639 0.02060 -0.1005 0.7325 0.9888
0.500 0.5232 0.02618 0.02032 -0.1091 0.7320 0.9964
0.750 0.5717 0.02592 0.02000 -0.1132 0.7310 1.0000
1.000 0.5980 0.02580 0.01982 -0.1128 0.7298 1.0000
1.250 0.5585 0.02756 0.02164 -0.1034 0.7178 1.0000
1.500 0.5425 0.02853 0.02262 -0.0969 0.7106 1.0000
1.750 0.6072 0.02739 0.02141 -0.1020 0.7141 1.0000
2.000 0.5659 0.02875 0.02279 -0.0917 0.7026 1.0000
2.250 0.5686 0.02911 0.02313 -0.0877 0.6981 1.0000
2.500 0.6230 0.02835 0.02235 -0.0914 0.6997 1.0000
2.750 0.5123 0.03090 0.02487 -0.0709 0.6785 1.0000
3.000 0.5384 0.03094 0.02490 -0.0707 0.6755 1.0000
3.250 0.5714 0.03077 0.02472 -0.0713 0.6740 1.0000
3.500 0.6087 0.03041 0.02435 -0.0725 0.6729 1.0000
3.750 0.6459 0.03007 0.02403 -0.0737 0.6721 1.0000
4.000 0.6850 0.02965 0.02362 -0.0751 0.6713 1.0000
4.250 0.6674 0.03117 0.02514 -0.0695 0.6589 1.0000
4.500 0.6952 0.03114 0.02512 -0.0695 0.6559 1.0000
4.750 0.7439 0.03012 0.02416 -0.0718 0.6574 1.0000
5.250 0.7373 0.03290 0.02695 -0.0654 0.6348 1.0000
5.500 0.7700 0.03251 0.02661 -0.0658 0.6326 1.0000
5.750 0.8058 0.03191 0.02609 -0.0665 0.6313 1.0000
6.000 0.8434 0.03118 0.02543 -0.0674 0.6304 1.0000
6.250 0.8817 0.03033 0.02465 -0.0682 0.6297 1.0000
6.500 0.9209 0.02935 0.02378 -0.0691 0.6291 1.0000
7.000 0.9268 0.03183 0.02635 -0.0645 0.6063 1.0000
7.250 0.9634 0.03086 0.02549 -0.0651 0.6047 1.0000
7.500 1.0390 0.02686 0.02169 -0.0685 0.6140 1.0000
7.750 1.0800 0.02392 0.01884 -0.0681 0.6044 1.0000
8.000 1.1294 0.02050 0.01548 -0.0684 0.5902 1.0000
8.250 1.1563 0.01970 0.01474 -0.0677 0.5744 1.0000
8.500 1.1788 0.01945 0.01452 -0.0667 0.5555 1.0000
8.750 1.2006 0.01921 0.01425 -0.0655 0.5273 1.0000
9.000 1.2155 0.01947 0.01435 -0.0636 0.4876 1.0000
9.250 1.2161 0.02072 0.01527 -0.0604 0.4333 1.0000
9.500 1.2055 0.02286 0.01704 -0.0566 0.3761 1.0000
9.750 1.1886 0.02559 0.01938 -0.0526 0.3153 1.0000
10.000 1.1653 0.02894 0.02224 -0.0484 0.2454 1.0000
10.250 1.1393 0.03270 0.02542 -0.0444 0.1635 1.0000
10.500 1.1206 0.03616 0.02837 -0.0412 0.0995 1.0000
10.750 1.1094 0.03929 0.03120 -0.0386 0.0698 1.0000
11.000 1.1076 0.04178 0.03365 -0.0369 0.0585 1.0000
11.250 1.1111 0.04389 0.03583 -0.0355 0.0526 1.0000
11.500 1.1109 0.04635 0.03827 -0.0341 0.0479 1.0000
11.750 1.1143 0.04852 0.04053 -0.0328 0.0453 1.0000
12.000 1.1205 0.05046 0.04254 -0.0317 0.0417 1.0000
12.250 1.1264 0.05240 0.04451 -0.0306 0.0394 1.0000
12.500 1.1305 0.05436 0.04644 -0.0290 0.0365 1.0000
12.750 1.1422 0.05577 0.04795 -0.0279 0.0348 1.0000
13.000 1.1557 0.05699 0.04923 -0.0267 0.0334 1.0000
13.250 1.1700 0.05815 0.05044 -0.0255 0.0320 1.0000
13.500 1.1841 0.05936 0.05164 -0.0244 0.0300 1.0000
13.750 1.2095 0.05996 0.05228 -0.0227 0.0282 1.0000
14.000 1.2240 0.06151 0.05403 -0.0217 0.0273 1.0000
14.250 1.2399 0.06318 0.05590 -0.0207 0.0265 1.0000
14.500 1.2559 0.06513 0.05806 -0.0196 0.0261 1.0000
14.750 1.2669 0.06765 0.06083 -0.0185 0.0256 1.0000
15.000 1.2710 0.07012 0.06346 -0.0177 0.0247 1.0000
15.250 1.2739 0.07344 0.06706 -0.0167 0.0245 1.0000
15.500 1.2790 0.07540 0.06899 -0.0166 0.0232 1.0000
15.750 1.2778 0.07905 0.07290 -0.0158 0.0232 1.0000
16.000 1.2739 0.08280 0.07685 -0.0152 0.0229 1.0000
16.250 1.2649 0.08712 0.08142 -0.0148 0.0229 1.0000
16.500 1.2553 0.09159 0.08609 -0.0148 0.0227 1.0000
16.750 1.2189 0.09929 0.09433 -0.0157 0.0238 1.0000
17.000 1.1847 0.10778 0.10322 -0.0177 0.0245 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 81-K-144/17 (ah81k144-il)