AH 79-K-143/18 (ah79k143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-143/18 (ah79k143-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.93 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k143-il-1000000.txt Download as CSV file: xf-ah79k143-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3825 0.06168 0.05908 -0.0950 0.7886 0.0091
-13.250 -0.4003 0.05295 0.05028 -0.0994 0.7884 0.0091
-13.000 -0.5558 0.05132 0.04838 -0.1111 0.7900 0.0086
-12.750 -0.5600 0.04715 0.04409 -0.1148 0.7893 0.0086
-12.500 -0.6046 0.03944 0.03603 -0.1171 0.7883 0.0085
-12.250 -0.6362 0.03428 0.03051 -0.1156 0.7874 0.0082
-12.000 -0.6188 0.03394 0.03014 -0.1154 0.7867 0.0085
-11.750 -0.6320 0.03093 0.02688 -0.1124 0.7860 0.0085
-11.500 -0.6297 0.02932 0.02513 -0.1101 0.7850 0.0085
-11.250 -0.6428 0.02613 0.02159 -0.1057 0.7837 0.0084
-11.000 -0.6331 0.02520 0.02054 -0.1036 0.7825 0.0086
-10.750 -0.6264 0.02393 0.01911 -0.1009 0.7814 0.0087
-10.500 -0.6191 0.02275 0.01776 -0.0980 0.7802 0.0088
-10.250 -0.6096 0.02163 0.01650 -0.0954 0.7792 0.0088
-10.000 -0.5947 0.02097 0.01571 -0.0935 0.7784 0.0090
-9.750 -0.5794 0.02002 0.01463 -0.0918 0.7775 0.0090
-9.500 -0.5629 0.01913 0.01362 -0.0903 0.7767 0.0090
-9.250 -0.5521 0.01744 0.01176 -0.0878 0.7759 0.0096
-9.000 -0.5325 0.01692 0.01119 -0.0867 0.7751 0.0099
-8.750 -0.5121 0.01645 0.01067 -0.0856 0.7744 0.0103
-8.500 -0.4925 0.01590 0.01003 -0.0844 0.7736 0.0103
-8.250 -0.4722 0.01548 0.00956 -0.0832 0.7727 0.0107
-8.000 -0.4496 0.01518 0.00922 -0.0825 0.7719 0.0113
-7.750 -0.4285 0.01472 0.00872 -0.0814 0.7708 0.0116
-7.500 -0.4056 0.01443 0.00839 -0.0807 0.7696 0.0119
-7.250 -0.3867 0.01376 0.00768 -0.0793 0.7683 0.0128
-7.000 -0.3636 0.01348 0.00739 -0.0786 0.7671 0.0139
-6.750 -0.3404 0.01316 0.00705 -0.0779 0.7659 0.0146
-6.500 -0.3170 0.01285 0.00669 -0.0772 0.7647 0.0158
-6.250 -0.2944 0.01243 0.00627 -0.0764 0.7635 0.0180
-6.000 -0.2692 0.01222 0.00602 -0.0760 0.7624 0.0198
-5.750 -0.2468 0.01176 0.00555 -0.0752 0.7614 0.0223
-5.500 -0.2220 0.01154 0.00530 -0.0747 0.7606 0.0242
-5.250 -0.1975 0.01128 0.00502 -0.0742 0.7597 0.0263
-5.000 -0.1731 0.01107 0.00480 -0.0737 0.7587 0.0289
-4.750 -0.1487 0.01089 0.00462 -0.0732 0.7574 0.0326
-4.500 -0.1247 0.01065 0.00443 -0.0726 0.7561 0.0399
-4.250 -0.1014 0.01038 0.00425 -0.0719 0.7546 0.0555
-4.000 -0.0771 0.01016 0.00410 -0.0714 0.7531 0.0719
-3.750 -0.0527 0.00991 0.00394 -0.0709 0.7517 0.0921
-3.500 -0.0278 0.00968 0.00378 -0.0705 0.7502 0.1138
-3.250 -0.0031 0.00942 0.00362 -0.0701 0.7490 0.1419
-3.000 0.0213 0.00910 0.00344 -0.0696 0.7477 0.1825
-2.750 0.0447 0.00871 0.00324 -0.0690 0.7464 0.2446
-2.500 0.0663 0.00819 0.00302 -0.0681 0.7449 0.3352
-2.250 0.0836 0.00755 0.00283 -0.0664 0.7430 0.4727
-2.000 0.0956 0.00675 0.00266 -0.0635 0.7407 0.6444
-1.750 0.1130 0.00631 0.00263 -0.0613 0.7386 0.7548
-1.500 0.1382 0.00628 0.00273 -0.0606 0.7366 0.8056
-1.250 0.1660 0.00631 0.00277 -0.0605 0.7348 0.8222
-1.000 0.1942 0.00634 0.00276 -0.0605 0.7331 0.8345
-0.750 0.2229 0.00643 0.00283 -0.0605 0.7315 0.8427
-0.500 0.2511 0.00646 0.00281 -0.0606 0.7297 0.8494
-0.250 0.2788 0.00656 0.00292 -0.0605 0.7273 0.8537
0.000 0.3062 0.00670 0.00309 -0.0603 0.7247 0.8596
0.250 0.3333 0.00685 0.00323 -0.0600 0.7221 0.8670
0.500 0.3608 0.00704 0.00344 -0.0595 0.7196 0.8719
0.750 0.3883 0.00715 0.00354 -0.0593 0.7172 0.8774
1.000 0.4164 0.00720 0.00354 -0.0594 0.7146 0.8812
1.250 0.4425 0.00715 0.00353 -0.0591 0.7109 0.8826
1.500 0.4695 0.00712 0.00351 -0.0590 0.7072 0.8840
1.750 0.4968 0.00710 0.00347 -0.0588 0.7035 0.8857
2.000 0.5240 0.00710 0.00346 -0.0588 0.6999 0.8875
2.250 0.5505 0.00710 0.00349 -0.0586 0.6947 0.8895
2.500 0.5776 0.00708 0.00346 -0.0586 0.6896 0.8915
2.750 0.6047 0.00709 0.00345 -0.0586 0.6841 0.8936
3.000 0.6322 0.00711 0.00348 -0.0587 0.6777 0.8953
3.250 0.6577 0.00705 0.00340 -0.0584 0.6715 0.8966
3.500 0.6833 0.00703 0.00341 -0.0580 0.6636 0.8978
3.750 0.7085 0.00704 0.00341 -0.0576 0.6560 0.8989
4.000 0.7338 0.00706 0.00344 -0.0572 0.6462 0.9000
4.250 0.7575 0.00712 0.00346 -0.0564 0.6317 0.9012
4.500 0.7791 0.00724 0.00350 -0.0553 0.6118 0.9025
5.000 0.8247 0.00747 0.00368 -0.0536 0.5810 0.9056
5.250 0.8464 0.00763 0.00380 -0.0526 0.5630 0.9073
5.500 0.8613 0.00800 0.00401 -0.0502 0.5250 0.9092
5.750 0.8740 0.00832 0.00419 -0.0475 0.4886 0.9109
6.000 0.8849 0.00866 0.00439 -0.0443 0.4527 0.9123
6.250 0.8969 0.00899 0.00461 -0.0415 0.4241 0.9137
6.500 0.9009 0.00949 0.00492 -0.0371 0.3814 0.9156
6.750 0.9042 0.00985 0.00517 -0.0325 0.3514 0.9179
7.000 0.8998 0.01043 0.00558 -0.0266 0.3116 0.9212
7.250 0.8941 0.01118 0.00613 -0.0208 0.2723 0.9234
7.500 0.8851 0.01208 0.00684 -0.0149 0.2293 0.9258
7.750 0.8795 0.01319 0.00778 -0.0104 0.1904 0.9282
8.000 0.8785 0.01424 0.00864 -0.0066 0.1525 0.9303
8.250 0.8763 0.01545 0.00960 -0.0029 0.1042 0.9324
8.500 0.8784 0.01660 0.01054 0.0001 0.0659 0.9342
8.750 0.8869 0.01752 0.01134 0.0021 0.0444 0.9358
9.000 0.8986 0.01834 0.01209 0.0036 0.0324 0.9369
9.250 0.9117 0.01915 0.01287 0.0048 0.0231 0.9377
9.500 0.9292 0.01989 0.01359 0.0052 0.0195 0.9387
9.750 0.9471 0.02064 0.01435 0.0055 0.0162 0.9396
10.000 0.9641 0.02147 0.01521 0.0058 0.0151 0.9405
10.250 0.9814 0.02231 0.01609 0.0061 0.0141 0.9413
10.500 0.9992 0.02312 0.01694 0.0063 0.0131 0.9421
10.750 1.0138 0.02417 0.01803 0.0067 0.0120 0.9430
11.000 1.0288 0.02522 0.01913 0.0070 0.0118 0.9438
11.250 1.0457 0.02615 0.02012 0.0071 0.0118 0.9446
11.500 1.0544 0.02771 0.02176 0.0079 0.0110 0.9455
11.750 1.0700 0.02876 0.02286 0.0080 0.0107 0.9462
12.000 1.0816 0.03016 0.02433 0.0084 0.0107 0.9470
12.250 1.0939 0.03156 0.02580 0.0086 0.0106 0.9478
12.500 1.1088 0.03278 0.02707 0.0086 0.0100 0.9485
12.750 1.1180 0.03447 0.02885 0.0090 0.0101 0.9493
13.000 1.1312 0.03585 0.03028 0.0090 0.0098 0.9500
13.250 1.1417 0.03754 0.03204 0.0092 0.0096 0.9507
13.500 1.1563 0.03903 0.03357 0.0087 0.0091 0.9514
13.750 1.1679 0.04076 0.03537 0.0084 0.0091 0.9522
14.000 1.1746 0.04295 0.03763 0.0084 0.0089 0.9531
14.250 1.1820 0.04510 0.03986 0.0084 0.0087 0.9540
14.500 1.1810 0.04784 0.04270 0.0092 0.0085 0.9550
14.750 1.1840 0.05018 0.04514 0.0099 0.0084 0.9559
15.000 1.1946 0.05214 0.04720 0.0095 0.0083 0.9570
15.250 1.2034 0.05424 0.04939 0.0092 0.0083 0.9580
15.500 1.2110 0.05649 0.05175 0.0089 0.0082 0.9590
15.750 1.2175 0.05881 0.05416 0.0088 0.0081 0.9600
16.000 1.2213 0.06139 0.05686 0.0089 0.0081 0.9610
16.250 1.2311 0.06385 0.05941 0.0074 0.0079 0.9623
16.500 1.2317 0.06691 0.06262 0.0075 0.0079 0.9633
16.750 1.2351 0.06996 0.06580 0.0066 0.0079 0.9645
17.000 1.2395 0.07321 0.06916 0.0051 0.0077 0.9659
17.250 1.2393 0.07679 0.07289 0.0042 0.0078 0.9673
17.500 1.2404 0.08059 0.07681 0.0025 0.0076 0.9689
17.750 1.2362 0.08495 0.08133 0.0011 0.0076 0.9704
18.000 1.2338 0.08930 0.08582 -0.0008 0.0075 0.9719
18.500 1.2276 0.09875 0.09552 -0.0057 0.0072 0.9762
18.750 1.2171 0.10465 0.10160 -0.0085 0.0072 0.9787
19.000 1.2063 0.11060 0.10771 -0.0113 0.0072 0.9968
19.250 1.1976 0.11656 0.11381 -0.0149 0.0071 0.9961
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Polar data table (+)
Polar graphs
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