AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 500,000 Max Cl/Cd: 103.74 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100a-il-500000-n5.txt Download as CSV file: xf-ah79100a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4167 0.10796 0.10549 -0.0350 1.0000 0.0083
-11.000 -0.4215 0.10258 0.10015 -0.0368 1.0000 0.0083
-10.500 -0.6835 0.04714 0.04472 -0.0620 1.0000 0.0077
-10.250 -0.6673 0.03082 0.02759 -0.0927 0.9871 0.0078
-10.000 -0.6429 0.02664 0.02295 -0.0987 0.9817 0.0080
-9.750 -0.6151 0.02381 0.01975 -0.1024 0.9782 0.0082
-9.500 -0.5877 0.02183 0.01747 -0.1047 0.9736 0.0084
-9.250 -0.5576 0.02026 0.01566 -0.1068 0.9703 0.0086
-9.000 -0.5268 0.01862 0.01382 -0.1091 0.9675 0.0089
-8.750 -0.4992 0.01770 0.01278 -0.1100 0.9619 0.0093
-8.500 -0.4686 0.01694 0.01191 -0.1113 0.9580 0.0097
-8.250 -0.4368 0.01625 0.01111 -0.1127 0.9546 0.0102
-8.000 -0.4091 0.01554 0.01027 -0.1132 0.9486 0.0109
-7.750 -0.3797 0.01482 0.00940 -0.1139 0.9433 0.0115
-7.500 -0.3507 0.01400 0.00845 -0.1147 0.9384 0.0121
-7.250 -0.3233 0.01346 0.00786 -0.1149 0.9320 0.0129
-7.000 -0.2946 0.01299 0.00730 -0.1153 0.9265 0.0138
-6.750 -0.2672 0.01255 0.00676 -0.1154 0.9201 0.0149
-6.500 -0.2396 0.01208 0.00619 -0.1154 0.9129 0.0159
-6.250 -0.2124 0.01162 0.00567 -0.1155 0.9051 0.0172
-6.000 -0.1850 0.01131 0.00528 -0.1154 0.8972 0.0187
-5.750 -0.1575 0.01104 0.00493 -0.1154 0.8900 0.0202
-5.500 -0.1301 0.01065 0.00449 -0.1154 0.8836 0.0222
-5.250 -0.1023 0.01039 0.00419 -0.1154 0.8779 0.0245
-5.000 -0.0747 0.01015 0.00388 -0.1154 0.8715 0.0263
-4.500 -0.0192 0.00961 0.00325 -0.1153 0.8591 0.0323
-4.250 0.0086 0.00941 0.00298 -0.1153 0.8524 0.0356
-4.000 0.0363 0.00917 0.00273 -0.1152 0.8455 0.0420
-3.750 0.0641 0.00897 0.00251 -0.1152 0.8385 0.0509
-3.500 0.0919 0.00877 0.00231 -0.1152 0.8321 0.0643
-3.250 0.1197 0.00858 0.00214 -0.1151 0.8251 0.0810
-3.000 0.1475 0.00837 0.00198 -0.1151 0.8185 0.1057
-2.750 0.1751 0.00812 0.00183 -0.1151 0.8108 0.1445
-2.500 0.2025 0.00782 0.00169 -0.1152 0.8028 0.2052
-2.250 0.2299 0.00756 0.00159 -0.1152 0.7938 0.2669
-2.000 0.2575 0.00743 0.00153 -0.1151 0.7855 0.3061
-1.750 0.2851 0.00733 0.00147 -0.1150 0.7769 0.3392
-1.500 0.3128 0.00724 0.00146 -0.1149 0.7681 0.3775
-1.250 0.3404 0.00721 0.00143 -0.1147 0.7586 0.3993
-1.000 0.3679 0.00719 0.00141 -0.1145 0.7470 0.4227
-0.750 0.3952 0.00718 0.00140 -0.1143 0.7343 0.4449
-0.500 0.4227 0.00719 0.00139 -0.1141 0.7224 0.4577
-0.250 0.4502 0.00721 0.00140 -0.1139 0.7110 0.4727
0.000 0.4775 0.00724 0.00140 -0.1137 0.6991 0.4866
0.250 0.5047 0.00729 0.00142 -0.1134 0.6846 0.4988
0.500 0.5316 0.00734 0.00145 -0.1131 0.6684 0.5120
0.750 0.5584 0.00741 0.00149 -0.1128 0.6516 0.5254
1.000 0.5853 0.00749 0.00154 -0.1125 0.6364 0.5379
1.250 0.6122 0.00757 0.00160 -0.1122 0.6222 0.5492
1.750 0.6651 0.00779 0.00175 -0.1115 0.5867 0.5767
2.000 0.6914 0.00790 0.00185 -0.1111 0.5698 0.5913
2.250 0.7178 0.00801 0.00196 -0.1108 0.5549 0.6058
2.500 0.7440 0.00814 0.00207 -0.1104 0.5388 0.6207
2.750 0.7698 0.00829 0.00220 -0.1099 0.5181 0.6359
3.000 0.7951 0.00847 0.00234 -0.1094 0.4951 0.6534
3.250 0.8207 0.00861 0.00250 -0.1089 0.4756 0.6748
3.500 0.8462 0.00872 0.00265 -0.1084 0.4587 0.7019
3.750 0.8709 0.00883 0.00283 -0.1078 0.4392 0.7408
4.000 0.8936 0.00888 0.00302 -0.1067 0.4189 0.8097
4.250 0.9233 0.00890 0.00318 -0.1071 0.3918 1.0000
4.500 0.9480 0.00924 0.00340 -0.1065 0.3642 1.0000
4.750 0.9719 0.00966 0.00366 -0.1059 0.3307 1.0000
5.000 0.9958 0.01007 0.00395 -0.1053 0.3005 1.0000
5.250 1.0198 0.01048 0.00424 -0.1047 0.2712 1.0000
5.500 1.0435 0.01091 0.00455 -0.1040 0.2435 1.0000
5.750 1.0650 0.01157 0.00497 -0.1031 0.1988 1.0000
6.000 1.0854 0.01233 0.00547 -0.1020 0.1504 1.0000
6.250 1.1062 0.01303 0.00595 -0.1010 0.1150 1.0000
6.500 1.1289 0.01353 0.00637 -0.1003 0.0953 1.0000
6.750 1.1507 0.01410 0.00683 -0.0994 0.0756 1.0000
7.000 1.1725 0.01466 0.00732 -0.0985 0.0584 1.0000
7.250 1.1936 0.01527 0.00784 -0.0975 0.0440 1.0000
7.500 1.2145 0.01587 0.00838 -0.0965 0.0328 1.0000
7.750 1.2353 0.01646 0.00895 -0.0954 0.0239 1.0000
8.000 1.2555 0.01708 0.00955 -0.0942 0.0182 1.0000
8.250 1.2757 0.01768 0.01017 -0.0931 0.0153 1.0000
8.500 1.2954 0.01830 0.01083 -0.0918 0.0136 1.0000
8.750 1.3150 0.01889 0.01148 -0.0906 0.0125 1.0000
9.000 1.3333 0.01955 0.01218 -0.0892 0.0115 1.0000
9.250 1.3500 0.02030 0.01298 -0.0875 0.0106 1.0000
9.500 1.3657 0.02102 0.01379 -0.0857 0.0100 1.0000
9.750 1.3801 0.02172 0.01457 -0.0837 0.0097 1.0000
10.000 1.3932 0.02249 0.01541 -0.0815 0.0093 1.0000
10.250 1.4055 0.02330 0.01630 -0.0793 0.0089 1.0000
10.500 1.4167 0.02420 0.01727 -0.0770 0.0086 1.0000
10.750 1.4272 0.02516 0.01832 -0.0748 0.0084 1.0000
11.000 1.4366 0.02623 0.01946 -0.0726 0.0082 1.0000
11.250 1.4442 0.02746 0.02079 -0.0704 0.0079 1.0000
11.500 1.4495 0.02892 0.02234 -0.0680 0.0077 1.0000
11.750 1.4526 0.03061 0.02414 -0.0657 0.0075 1.0000
12.000 1.4563 0.03234 0.02597 -0.0637 0.0074 1.0000
12.250 1.4620 0.03398 0.02772 -0.0620 0.0072 1.0000
12.500 1.4679 0.03565 0.02950 -0.0605 0.0071 1.0000
12.750 1.4724 0.03752 0.03149 -0.0591 0.0069 1.0000
13.000 1.4758 0.03957 0.03366 -0.0578 0.0068 1.0000
13.250 1.4786 0.04178 0.03599 -0.0567 0.0066 1.0000
13.500 1.4812 0.04408 0.03840 -0.0558 0.0064 1.0000
13.750 1.4811 0.04677 0.04124 -0.0551 0.0063 1.0000
14.000 1.4800 0.04972 0.04432 -0.0546 0.0062 1.0000
14.250 1.4788 0.05278 0.04750 -0.0544 0.0061 1.0000
14.500 1.4761 0.05617 0.05102 -0.0544 0.0060 1.0000
14.750 1.4728 0.05980 0.05479 -0.0548 0.0059 1.0000
15.000 1.4684 0.06375 0.05886 -0.0554 0.0059 1.0000
15.250 1.4637 0.06790 0.06315 -0.0563 0.0058 1.0000
15.500 1.4579 0.07242 0.06780 -0.0576 0.0057 1.0000
15.750 1.4506 0.07734 0.07286 -0.0592 0.0057 1.0000
16.000 1.4427 0.08253 0.07818 -0.0610 0.0056 1.0000
16.250 1.4335 0.08810 0.08390 -0.0633 0.0056 1.0000
16.500 1.4239 0.09396 0.08990 -0.0658 0.0055 1.0000
16.750 1.4131 0.10020 0.09628 -0.0686 0.0055 1.0000
17.000 1.4018 0.10671 0.10293 -0.0718 0.0055 1.0000
17.250 1.3902 0.11346 0.10982 -0.0752 0.0054 1.0000
17.500 1.3779 0.12054 0.11703 -0.0789 0.0054 1.0000
17.750 1.3655 0.12780 0.12443 -0.0829 0.0054 1.0000
18.000 1.3533 0.13517 0.13195 -0.0871 0.0054 1.0000
18.250 1.3408 0.14282 0.13973 -0.0916 0.0053 1.0000
18.500 1.3286 0.15059 0.14764 -0.0963 0.0053 1.0000
18.750 1.3164 0.15858 0.15576 -0.1012 0.0053 1.0000
19.000 1.3041 0.16676 0.16407 -0.1064 0.0053 1.0000
19.250 1.2914 0.17536 0.17279 -0.1120 0.0053 1.0000
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