AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.03 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100a-il-1000000.txt Download as CSV file: xf-ah79100a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.3372 0.15683 0.15522 -0.0191 1.0000 0.0090
-15.750 -0.3312 0.15465 0.15304 -0.0204 1.0000 0.0091
-15.500 -0.4752 0.17363 0.17179 -0.0128 1.0000 0.0088
-15.250 -0.4684 0.17052 0.16868 -0.0139 1.0000 0.0088
-15.000 -0.4610 0.16774 0.16590 -0.0148 1.0000 0.0089
-14.750 -0.4538 0.16505 0.16322 -0.0158 1.0000 0.0092
-14.500 -0.4477 0.16182 0.15999 -0.0170 1.0000 0.0092
-14.250 -0.4414 0.15881 0.15699 -0.0181 1.0000 0.0095
-10.250 -0.6645 0.03335 0.03111 -0.0878 0.9945 0.0083
-10.000 -0.6386 0.02692 0.02415 -0.0986 0.9896 0.0084
-9.750 -0.6102 0.02408 0.02099 -0.1027 0.9862 0.0086
-9.500 -0.5835 0.01957 0.01594 -0.1075 0.9826 0.0088
-9.250 -0.5517 0.01755 0.01368 -0.1104 0.9809 0.0092
-9.000 -0.5183 0.01644 0.01245 -0.1125 0.9796 0.0095
-8.750 -0.4892 0.01572 0.01164 -0.1134 0.9751 0.0098
-8.500 -0.4581 0.01490 0.01071 -0.1147 0.9717 0.0101
-8.250 -0.4260 0.01407 0.00976 -0.1162 0.9689 0.0105
-8.000 -0.3977 0.01332 0.00890 -0.1167 0.9635 0.0109
-7.750 -0.3691 0.01268 0.00816 -0.1172 0.9579 0.0113
-7.500 -0.3403 0.01216 0.00752 -0.1175 0.9522 0.0116
-7.250 -0.3152 0.01113 0.00636 -0.1174 0.9436 0.0125
-7.000 -0.2881 0.01082 0.00602 -0.1174 0.9361 0.0134
-6.750 -0.2610 0.01059 0.00574 -0.1172 0.9287 0.0146
-6.500 -0.2333 0.01042 0.00551 -0.1171 0.9228 0.0155
-6.250 -0.2071 0.00968 0.00469 -0.1171 0.9159 0.0175
-5.750 -0.1521 0.00926 0.00418 -0.1169 0.9037 0.0203
-5.500 -0.1250 0.00878 0.00361 -0.1168 0.8975 0.0225
-5.250 -0.0973 0.00855 0.00335 -0.1168 0.8913 0.0243
-5.000 -0.0697 0.00838 0.00312 -0.1167 0.8844 0.0260
-4.750 -0.0420 0.00814 0.00282 -0.1166 0.8783 0.0281
-4.500 -0.0143 0.00791 0.00257 -0.1166 0.8719 0.0317
-4.250 0.0136 0.00777 0.00237 -0.1165 0.8661 0.0343
-4.000 0.0415 0.00749 0.00210 -0.1164 0.8599 0.0417
-3.750 0.0694 0.00728 0.00189 -0.1164 0.8535 0.0535
-3.500 0.0972 0.00709 0.00172 -0.1163 0.8470 0.0713
-3.250 0.1249 0.00685 0.00156 -0.1163 0.8396 0.1003
-3.000 0.1525 0.00657 0.00142 -0.1163 0.8330 0.1475
-2.750 0.1801 0.00630 0.00130 -0.1164 0.8260 0.2010
-2.500 0.2077 0.00608 0.00120 -0.1163 0.8195 0.2554
-2.250 0.2355 0.00589 0.00114 -0.1163 0.8122 0.3034
-2.000 0.2631 0.00578 0.00109 -0.1162 0.8046 0.3429
-1.750 0.2909 0.00569 0.00106 -0.1161 0.7955 0.3778
-1.500 0.3188 0.00565 0.00104 -0.1160 0.7871 0.3986
-1.250 0.3466 0.00562 0.00102 -0.1159 0.7783 0.4179
-1.000 0.3746 0.00560 0.00101 -0.1158 0.7700 0.4392
-0.750 0.4023 0.00560 0.00099 -0.1157 0.7606 0.4552
-0.500 0.4300 0.00559 0.00100 -0.1155 0.7493 0.4719
-0.250 0.4576 0.00559 0.00100 -0.1153 0.7371 0.4895
0.000 0.4852 0.00562 0.00101 -0.1152 0.7248 0.5014
0.250 0.5126 0.00565 0.00102 -0.1150 0.7128 0.5148
0.500 0.5400 0.00569 0.00105 -0.1147 0.6998 0.5286
0.750 0.5672 0.00574 0.00108 -0.1145 0.6846 0.5416
1.000 0.5943 0.00580 0.00112 -0.1143 0.6679 0.5551
1.250 0.6213 0.00587 0.00117 -0.1140 0.6509 0.5692
1.500 0.6482 0.00595 0.00123 -0.1137 0.6349 0.5833
1.750 0.6750 0.00604 0.00129 -0.1134 0.6175 0.5976
2.000 0.7013 0.00616 0.00137 -0.1130 0.5969 0.6119
2.250 0.7278 0.00627 0.00146 -0.1127 0.5761 0.6288
2.500 0.7540 0.00639 0.00155 -0.1123 0.5569 0.6484
2.750 0.7804 0.00648 0.00166 -0.1120 0.5409 0.6707
3.000 0.8066 0.00657 0.00177 -0.1116 0.5248 0.6979
3.500 0.8571 0.00665 0.00204 -0.1105 0.4912 0.7966
3.750 0.8866 0.00647 0.00215 -0.1108 0.4695 1.0000
4.000 0.9125 0.00671 0.00229 -0.1104 0.4461 1.0000
4.250 0.9379 0.00699 0.00245 -0.1100 0.4180 1.0000
4.500 0.9635 0.00726 0.00262 -0.1095 0.3921 1.0000
4.750 0.9890 0.00752 0.00280 -0.1091 0.3696 1.0000
5.000 1.0135 0.00789 0.00302 -0.1086 0.3364 1.0000
5.250 1.0364 0.00840 0.00331 -0.1078 0.2902 1.0000
5.500 1.0593 0.00892 0.00362 -0.1070 0.2480 1.0000
5.750 1.0816 0.00950 0.00397 -0.1061 0.2039 1.0000
6.000 1.1037 0.01010 0.00435 -0.1053 0.1635 1.0000
6.250 1.1262 0.01063 0.00473 -0.1045 0.1334 1.0000
6.500 1.1491 0.01113 0.00510 -0.1037 0.1092 1.0000
6.750 1.1716 0.01165 0.00549 -0.1029 0.0873 1.0000
7.000 1.1939 0.01218 0.00592 -0.1020 0.0669 1.0000
7.250 1.2158 0.01273 0.00636 -0.1011 0.0493 1.0000
7.500 1.2365 0.01338 0.00690 -0.1000 0.0315 1.0000
7.750 1.2564 0.01412 0.00753 -0.0987 0.0183 1.0000
8.000 1.2772 0.01473 0.00814 -0.0976 0.0146 1.0000
8.250 1.2991 0.01521 0.00866 -0.0966 0.0133 1.0000
8.500 1.3205 0.01572 0.00921 -0.0956 0.0124 1.0000
8.750 1.3408 0.01630 0.00982 -0.0944 0.0115 1.0000
9.000 1.3581 0.01713 0.01071 -0.0927 0.0106 1.0000
9.250 1.3757 0.01786 0.01153 -0.0911 0.0102 1.0000
9.500 1.3944 0.01845 0.01218 -0.0897 0.0100 1.0000
9.750 1.4116 0.01913 0.01292 -0.0880 0.0097 1.0000
10.000 1.4273 0.01979 0.01365 -0.0862 0.0094 1.0000
10.250 1.4408 0.02046 0.01437 -0.0839 0.0090 1.0000
10.500 1.4538 0.02115 0.01511 -0.0817 0.0087 1.0000
10.750 1.4652 0.02194 0.01595 -0.0793 0.0084 1.0000
11.000 1.4746 0.02287 0.01696 -0.0767 0.0082 1.0000
11.250 1.4808 0.02405 0.01821 -0.0739 0.0079 1.0000
11.500 1.4828 0.02558 0.01985 -0.0708 0.0077 1.0000
11.750 1.4786 0.02770 0.02210 -0.0673 0.0075 1.0000
12.000 1.4825 0.02931 0.02382 -0.0649 0.0074 1.0000
12.250 1.4891 0.03076 0.02536 -0.0630 0.0073 1.0000
12.500 1.4961 0.03222 0.02692 -0.0613 0.0072 1.0000
12.750 1.5014 0.03390 0.02870 -0.0596 0.0071 1.0000
13.000 1.5050 0.03581 0.03071 -0.0580 0.0070 1.0000
13.250 1.5078 0.03787 0.03288 -0.0566 0.0069 1.0000
13.500 1.5112 0.03994 0.03506 -0.0554 0.0068 1.0000
13.750 1.5114 0.04246 0.03769 -0.0543 0.0067 1.0000
14.000 1.5102 0.04522 0.04058 -0.0534 0.0066 1.0000
14.250 1.5103 0.04794 0.04341 -0.0528 0.0065 1.0000
14.500 1.5082 0.05105 0.04663 -0.0524 0.0064 1.0000
14.750 1.5079 0.05403 0.04972 -0.0523 0.0063 1.0000
15.000 1.5041 0.05764 0.05345 -0.0525 0.0062 1.0000
15.250 1.5003 0.06141 0.05734 -0.0530 0.0061 1.0000
15.500 1.4958 0.06544 0.06148 -0.0538 0.0060 1.0000
15.750 1.4930 0.06939 0.06553 -0.0550 0.0059 1.0000
16.000 1.4872 0.07398 0.07023 -0.0564 0.0058 1.0000
16.250 1.4802 0.07891 0.07528 -0.0581 0.0058 1.0000
16.500 1.4701 0.08453 0.08103 -0.0603 0.0057 1.0000
16.750 1.4607 0.09026 0.08687 -0.0627 0.0057 1.0000
17.000 1.4499 0.09641 0.09315 -0.0655 0.0056 1.0000
17.250 1.4383 0.10287 0.09973 -0.0686 0.0056 1.0000
17.500 1.4250 0.10986 0.10685 -0.0721 0.0055 1.0000
17.750 1.4116 0.11710 0.11423 -0.0759 0.0055 1.0000
18.000 1.3978 0.12463 0.12190 -0.0801 0.0055 1.0000
18.250 1.3835 0.13241 0.12981 -0.0845 0.0055 1.0000
18.500 1.3691 0.14045 0.13798 -0.0893 0.0055 1.0000
18.750 1.3547 0.14874 0.14640 -0.0944 0.0055 1.0000
19.000 1.3405 0.15717 0.15496 -0.0997 0.0055 1.0000
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