AH 79-K-143/18 (ah79k143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-143/18 (ah79k143-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.14 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k143-il-1000000-n5.txt Download as CSV file: xf-ah79k143-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-143/18
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8581 0.04981 0.04633 -0.0915 0.7745 0.0049
-15.000 -0.8696 0.04415 0.04049 -0.0961 0.7740 0.0048
-14.750 -0.8864 0.03895 0.03507 -0.0990 0.7734 0.0049
-14.500 -0.8779 0.03698 0.03300 -0.1000 0.7727 0.0049
-14.250 -0.8863 0.03367 0.02948 -0.1000 0.7722 0.0049
-14.000 -0.8807 0.03183 0.02754 -0.0997 0.7716 0.0051
-13.750 -0.8752 0.03003 0.02561 -0.0991 0.7710 0.0050
-13.500 -0.8672 0.02844 0.02389 -0.0985 0.7703 0.0052
-13.250 -0.8550 0.02722 0.02256 -0.0979 0.7697 0.0052
-13.000 -0.8468 0.02564 0.02082 -0.0968 0.7690 0.0052
-12.750 -0.8334 0.02452 0.01959 -0.0959 0.7683 0.0052
-12.500 -0.8185 0.02352 0.01849 -0.0951 0.7675 0.0054
-12.250 -0.8059 0.02234 0.01717 -0.0939 0.7668 0.0054
-12.000 -0.7896 0.02151 0.01624 -0.0929 0.7661 0.0054
-11.750 -0.7731 0.02068 0.01532 -0.0919 0.7653 0.0056
-11.500 -0.7568 0.01990 0.01444 -0.0906 0.7645 0.0055
-11.250 -0.7396 0.01920 0.01365 -0.0894 0.7637 0.0057
-11.000 -0.7226 0.01854 0.01290 -0.0881 0.7629 0.0059
-10.750 -0.7046 0.01799 0.01228 -0.0869 0.7622 0.0061
-10.500 -0.6868 0.01741 0.01161 -0.0855 0.7615 0.0062
-10.250 -0.6674 0.01689 0.01101 -0.0844 0.7607 0.0062
-10.000 -0.6465 0.01639 0.01044 -0.0835 0.7600 0.0064
-9.750 -0.6258 0.01589 0.00984 -0.0827 0.7591 0.0065
-9.500 -0.6040 0.01542 0.00931 -0.0819 0.7581 0.0065
-9.250 -0.5827 0.01493 0.00876 -0.0811 0.7574 0.0067
-9.000 -0.5609 0.01446 0.00825 -0.0803 0.7567 0.0071
-8.750 -0.5385 0.01405 0.00782 -0.0796 0.7559 0.0074
-8.500 -0.5156 0.01369 0.00741 -0.0790 0.7550 0.0074
-8.250 -0.4926 0.01332 0.00701 -0.0783 0.7539 0.0078
-8.000 -0.4691 0.01302 0.00669 -0.0778 0.7530 0.0082
-7.750 -0.4456 0.01270 0.00634 -0.0772 0.7519 0.0087
-7.500 -0.4216 0.01243 0.00603 -0.0767 0.7510 0.0090
-7.250 -0.3978 0.01212 0.00571 -0.0761 0.7501 0.0098
-7.000 -0.3736 0.01187 0.00545 -0.0757 0.7492 0.0110
-6.750 -0.3492 0.01162 0.00518 -0.0752 0.7482 0.0116
-6.500 -0.3249 0.01137 0.00492 -0.0747 0.7472 0.0128
-6.250 -0.3002 0.01115 0.00469 -0.0743 0.7462 0.0143
-6.000 -0.2752 0.01095 0.00446 -0.0739 0.7451 0.0155
-5.750 -0.2507 0.01071 0.00420 -0.0735 0.7438 0.0169
-5.500 -0.2259 0.01050 0.00399 -0.0730 0.7423 0.0183
-5.250 -0.2007 0.01032 0.00380 -0.0727 0.7408 0.0195
-5.000 -0.1754 0.01014 0.00361 -0.0723 0.7395 0.0205
-4.750 -0.1504 0.00993 0.00343 -0.0720 0.7380 0.0232
-4.500 -0.1252 0.00974 0.00325 -0.0716 0.7366 0.0272
-4.250 -0.1001 0.00954 0.00308 -0.0712 0.7351 0.0335
-4.000 -0.0749 0.00934 0.00292 -0.0709 0.7338 0.0427
-3.750 -0.0496 0.00914 0.00277 -0.0706 0.7326 0.0536
-3.500 -0.0240 0.00897 0.00263 -0.0703 0.7312 0.0641
-3.250 0.0016 0.00880 0.00249 -0.0700 0.7299 0.0768
-3.000 0.0270 0.00863 0.00238 -0.0697 0.7283 0.0931
-2.750 0.0526 0.00846 0.00229 -0.0694 0.7263 0.1120
-2.500 0.0780 0.00828 0.00219 -0.0691 0.7236 0.1347
-2.250 0.1029 0.00806 0.00207 -0.0687 0.7207 0.1655
-2.000 0.1265 0.00775 0.00194 -0.0681 0.7180 0.2214
-1.750 0.1491 0.00738 0.00181 -0.0674 0.7159 0.2974
-1.500 0.1720 0.00705 0.00172 -0.0667 0.7136 0.3716
-1.250 0.1915 0.00653 0.00161 -0.0654 0.7107 0.4918
-1.000 0.2103 0.00602 0.00149 -0.0638 0.7075 0.6103
-0.750 0.2290 0.00558 0.00141 -0.0621 0.7045 0.7143
-0.500 0.2521 0.00543 0.00143 -0.0610 0.7015 0.7680
-0.250 0.2783 0.00544 0.00153 -0.0606 0.6981 0.8048
0.000 0.3054 0.00551 0.00164 -0.0605 0.6944 0.8231
0.250 0.3327 0.00561 0.00174 -0.0603 0.6907 0.8372
0.500 0.3597 0.00572 0.00182 -0.0601 0.6868 0.8472
0.750 0.3873 0.00582 0.00193 -0.0601 0.6823 0.8527
1.000 0.4149 0.00589 0.00200 -0.0601 0.6771 0.8559
1.250 0.4421 0.00593 0.00201 -0.0600 0.6718 0.8578
1.500 0.4697 0.00597 0.00204 -0.0601 0.6656 0.8599
1.750 0.4965 0.00601 0.00205 -0.0600 0.6583 0.8619
2.000 0.5236 0.00605 0.00207 -0.0600 0.6514 0.8639
2.500 0.5762 0.00617 0.00213 -0.0596 0.6340 0.8667
2.750 0.6018 0.00625 0.00218 -0.0593 0.6241 0.8678
3.000 0.6275 0.00633 0.00225 -0.0590 0.6143 0.8688
3.250 0.6532 0.00642 0.00232 -0.0587 0.6037 0.8698
3.500 0.6781 0.00653 0.00240 -0.0582 0.5924 0.8707
3.750 0.7025 0.00665 0.00249 -0.0577 0.5812 0.8718
4.000 0.7264 0.00678 0.00261 -0.0571 0.5677 0.8730
4.250 0.7480 0.00699 0.00274 -0.0560 0.5468 0.8744
4.500 0.7651 0.00734 0.00295 -0.0540 0.5115 0.8764
4.750 0.7848 0.00760 0.00313 -0.0526 0.4891 0.8780
5.000 0.8040 0.00786 0.00331 -0.0511 0.4656 0.8792
5.250 0.8248 0.00807 0.00348 -0.0499 0.4502 0.8801
5.500 0.8321 0.00865 0.00381 -0.0462 0.3994 0.8816
5.750 0.8380 0.00921 0.00417 -0.0422 0.3516 0.8833
6.000 0.8302 0.00999 0.00464 -0.0355 0.2893 0.8855
6.250 0.8252 0.01066 0.00510 -0.0295 0.2435 0.8875
6.500 0.8131 0.01166 0.00581 -0.0225 0.1849 0.8898
7.000 0.8225 0.01316 0.00710 -0.0159 0.1330 0.8930
7.250 0.8228 0.01424 0.00798 -0.0124 0.0949 0.8945
7.500 0.8268 0.01520 0.00879 -0.0094 0.0624 0.8958
7.750 0.8390 0.01589 0.00940 -0.0076 0.0458 0.8971
8.000 0.8542 0.01647 0.00995 -0.0064 0.0374 0.8980
8.250 0.8692 0.01709 0.01055 -0.0051 0.0302 0.8989
8.500 0.8852 0.01768 0.01112 -0.0041 0.0247 0.8997
8.750 0.9022 0.01825 0.01169 -0.0032 0.0203 0.9005
9.000 0.9183 0.01889 0.01231 -0.0023 0.0163 0.9014
9.250 0.9343 0.01956 0.01298 -0.0014 0.0135 0.9021
9.500 0.9522 0.02014 0.01358 -0.0008 0.0130 0.9029
9.750 0.9682 0.02086 0.01431 0.0000 0.0109 0.9037
10.000 0.9859 0.02149 0.01498 0.0005 0.0106 0.9044
10.250 1.0024 0.02222 0.01573 0.0012 0.0100 0.9052
10.500 1.0188 0.02296 0.01650 0.0017 0.0093 0.9059
10.750 1.0326 0.02389 0.01745 0.0025 0.0083 0.9066
11.000 1.0481 0.02473 0.01833 0.0031 0.0082 0.9073
11.250 1.0633 0.02559 0.01924 0.0037 0.0083 0.9079
11.500 1.0797 0.02641 0.02009 0.0041 0.0077 0.9085
11.750 1.0947 0.02732 0.02105 0.0046 0.0076 0.9091
12.000 1.1077 0.02837 0.02215 0.0053 0.0075 0.9096
12.250 1.1221 0.02942 0.02324 0.0056 0.0074 0.9102
12.500 1.1375 0.03050 0.02438 0.0057 0.0070 0.9109
12.750 1.1502 0.03185 0.02580 0.0060 0.0070 0.9116
13.000 1.1650 0.03302 0.02702 0.0060 0.0069 0.9123
13.250 1.1781 0.03434 0.02839 0.0061 0.0067 0.9132
13.500 1.1897 0.03582 0.02992 0.0063 0.0064 0.9140
13.750 1.2018 0.03726 0.03142 0.0064 0.0063 0.9147
14.000 1.2090 0.03914 0.03339 0.0068 0.0062 0.9154
14.250 1.2164 0.04103 0.03534 0.0071 0.0060 0.9161
14.500 1.2222 0.04312 0.03753 0.0074 0.0060 0.9167
14.750 1.2365 0.04444 0.03891 0.0072 0.0059 0.9174
15.000 1.2452 0.04633 0.04087 0.0072 0.0059 0.9181
15.250 1.2532 0.04827 0.04289 0.0072 0.0058 0.9190
15.500 1.2583 0.05051 0.04522 0.0073 0.0057 0.9199
15.750 1.2652 0.05262 0.04741 0.0073 0.0056 0.9207
16.000 1.2691 0.05509 0.04997 0.0072 0.0054 0.9214
16.250 1.2772 0.05713 0.05208 0.0069 0.0055 0.9221
16.500 1.2762 0.06017 0.05523 0.0069 0.0053 0.9228
16.750 1.2792 0.06280 0.05795 0.0067 0.0053 0.9234
17.000 1.2839 0.06531 0.06054 0.0063 0.0052 0.9240
17.500 1.2859 0.07159 0.06701 0.0049 0.0051 0.9255
17.750 1.2843 0.07507 0.07061 0.0041 0.0051 0.9262
18.000 1.2812 0.07878 0.07443 0.0033 0.0051 0.9270
18.250 1.2816 0.08218 0.07792 0.0022 0.0050 0.9278
18.500 1.2808 0.08576 0.08160 0.0011 0.0050 0.9287
18.750 1.2778 0.08970 0.08564 -0.0002 0.0049 0.9296
19.000 1.2695 0.09430 0.09038 -0.0016 0.0049 0.9304
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Polar data table (+)
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