RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 101 AIRFOIL (rae101-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.9 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae101-il-1000000.txt Download as CSV file: xf-rae101-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 101 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9318 0.09245 0.09054 -0.0033 1.0000 0.0075
-14.500 -0.9843 0.07646 0.07433 -0.0135 1.0000 0.0073
-14.250 -1.0143 0.06652 0.06422 -0.0201 1.0000 0.0073
-14.000 -1.0350 0.05899 0.05653 -0.0252 1.0000 0.0073
-13.750 -1.0527 0.05258 0.04995 -0.0293 1.0000 0.0073
-13.500 -1.0732 0.04643 0.04359 -0.0327 1.0000 0.0072
-13.250 -1.0850 0.04211 0.03910 -0.0344 1.0000 0.0073
-13.000 -1.0956 0.03848 0.03529 -0.0350 1.0000 0.0073
-12.750 -1.1015 0.03579 0.03246 -0.0345 1.0000 0.0074
-12.500 -1.1103 0.03314 0.02962 -0.0329 1.0000 0.0074
-12.250 -1.1154 0.03110 0.02742 -0.0304 1.0000 0.0075
-12.000 -1.1180 0.02943 0.02559 -0.0273 1.0000 0.0076
-11.750 -1.1160 0.02802 0.02404 -0.0243 1.0000 0.0077
-11.500 -1.1082 0.02657 0.02243 -0.0222 1.0000 0.0078
-11.250 -1.0979 0.02519 0.02090 -0.0203 1.0000 0.0079
-11.000 -1.0824 0.02431 0.01988 -0.0189 1.0000 0.0081
-10.750 -1.0694 0.02298 0.01839 -0.0172 1.0000 0.0084
-10.500 -1.0632 0.02066 0.01586 -0.0147 1.0000 0.0088
-10.250 -1.0458 0.01977 0.01490 -0.0134 1.0000 0.0091
-10.000 -1.0270 0.01900 0.01406 -0.0122 1.0000 0.0094
-9.750 -1.0075 0.01828 0.01327 -0.0111 1.0000 0.0097
-9.500 -0.9872 0.01763 0.01255 -0.0101 1.0000 0.0100
-9.250 -0.9673 0.01689 0.01172 -0.0089 1.0000 0.0104
-9.000 -0.9466 0.01626 0.01103 -0.0078 1.0000 0.0108
-8.750 -0.9255 0.01567 0.01037 -0.0068 1.0000 0.0111
-8.500 -0.9031 0.01526 0.00990 -0.0059 1.0000 0.0114
-8.250 -0.8873 0.01404 0.00855 -0.0040 1.0000 0.0121
-8.000 -0.8673 0.01337 0.00784 -0.0027 1.0000 0.0128
-7.750 -0.8449 0.01298 0.00742 -0.0017 1.0000 0.0136
-7.500 -0.8227 0.01257 0.00698 -0.0008 1.0000 0.0144
-7.250 -0.7996 0.01226 0.00665 0.0001 1.0000 0.0152
-7.000 -0.7775 0.01186 0.00619 0.0012 1.0000 0.0159
-6.750 -0.7576 0.01120 0.00549 0.0026 1.0000 0.0177
-6.500 -0.7351 0.01087 0.00515 0.0036 1.0000 0.0191
-6.250 -0.7124 0.01059 0.00484 0.0046 1.0000 0.0205
-6.000 -0.6907 0.01021 0.00442 0.0058 1.0000 0.0223
-5.750 -0.6690 0.00986 0.00409 0.0070 1.0000 0.0255
-5.500 -0.6466 0.00964 0.00385 0.0080 1.0000 0.0278
-5.250 -0.6213 0.00926 0.00348 0.0085 0.9994 0.0331
-5.000 -0.5855 0.00896 0.00320 0.0066 0.9970 0.0405
-4.750 -0.5496 0.00862 0.00294 0.0047 0.9942 0.0541
-4.500 -0.5164 0.00828 0.00268 0.0033 0.9901 0.0739
-4.250 -0.4819 0.00785 0.00242 0.0017 0.9859 0.1090
-4.000 -0.4482 0.00736 0.00216 0.0001 0.9815 0.1620
-3.750 -0.4166 0.00680 0.00189 -0.0010 0.9745 0.2324
-3.500 -0.3840 0.00618 0.00166 -0.0025 0.9670 0.3279
-3.250 -0.3501 0.00587 0.00152 -0.0039 0.9563 0.3819
-2.750 -0.2890 0.00553 0.00130 -0.0049 0.9201 0.4431
-2.500 -0.2620 0.00544 0.00121 -0.0046 0.8963 0.4677
-2.250 -0.2361 0.00538 0.00113 -0.0040 0.8707 0.4895
-2.000 -0.2101 0.00533 0.00107 -0.0035 0.8465 0.5118
-1.500 -0.1582 0.00526 0.00097 -0.0025 0.8015 0.5553
-1.250 -0.1321 0.00524 0.00093 -0.0020 0.7800 0.5771
-1.000 -0.1058 0.00521 0.00090 -0.0016 0.7595 0.5993
-0.750 -0.0794 0.00519 0.00088 -0.0012 0.7402 0.6209
-0.500 -0.0530 0.00517 0.00087 -0.0008 0.7220 0.6431
-0.250 -0.0265 0.00515 0.00086 -0.0004 0.7038 0.6641
0.000 0.0000 0.00514 0.00086 0.0000 0.6845 0.6845
0.250 0.0265 0.00515 0.00086 0.0004 0.6641 0.7038
0.500 0.0530 0.00517 0.00087 0.0008 0.6431 0.7219
0.750 0.0794 0.00519 0.00088 0.0012 0.6211 0.7402
1.000 0.1058 0.00521 0.00090 0.0016 0.5992 0.7596
1.250 0.1321 0.00524 0.00093 0.0020 0.5771 0.7801
1.500 0.1581 0.00526 0.00097 0.0025 0.5554 0.8016
2.000 0.2101 0.00533 0.00107 0.0035 0.5116 0.8465
2.250 0.2360 0.00538 0.00113 0.0041 0.4893 0.8707
2.500 0.2620 0.00543 0.00121 0.0046 0.4679 0.8965
2.750 0.2890 0.00552 0.00130 0.0049 0.4434 0.9202
3.250 0.3501 0.00586 0.00152 0.0039 0.3821 0.9563
3.500 0.3840 0.00618 0.00166 0.0025 0.3283 0.9669
3.750 0.4167 0.00678 0.00188 0.0010 0.2362 0.9745
4.000 0.4482 0.00735 0.00216 -0.0001 0.1622 0.9816
4.250 0.4821 0.00785 0.00242 -0.0017 0.1091 0.9860
4.500 0.5164 0.00828 0.00268 -0.0034 0.0736 0.9901
4.750 0.5497 0.00862 0.00294 -0.0047 0.0539 0.9942
5.000 0.5856 0.00897 0.00320 -0.0066 0.0403 0.9970
5.250 0.6216 0.00926 0.00348 -0.0085 0.0332 0.9995
5.500 0.6464 0.00963 0.00384 -0.0080 0.0278 1.0000
5.750 0.6688 0.00985 0.00408 -0.0069 0.0255 1.0000
6.000 0.6905 0.01021 0.00442 -0.0058 0.0224 1.0000
6.250 0.7122 0.01059 0.00484 -0.0046 0.0204 1.0000
6.500 0.7349 0.01087 0.00515 -0.0036 0.0191 1.0000
6.750 0.7574 0.01120 0.00549 -0.0026 0.0177 1.0000
7.000 0.7778 0.01180 0.00613 -0.0012 0.0161 1.0000
7.250 0.7994 0.01228 0.00666 -0.0001 0.0152 1.0000
7.500 0.8223 0.01260 0.00702 0.0008 0.0144 1.0000
7.750 0.8449 0.01297 0.00741 0.0017 0.0136 1.0000
8.000 0.8672 0.01338 0.00786 0.0027 0.0129 1.0000
8.250 0.8877 0.01400 0.00851 0.0039 0.0122 1.0000
8.500 0.9031 0.01527 0.00990 0.0059 0.0114 1.0000
8.750 0.9253 0.01571 0.01040 0.0068 0.0112 1.0000
9.000 0.9467 0.01627 0.01103 0.0078 0.0108 1.0000
9.250 0.9671 0.01694 0.01178 0.0089 0.0104 1.0000
9.500 0.9873 0.01764 0.01256 0.0100 0.0101 1.0000
9.750 1.0077 0.01828 0.01327 0.0111 0.0097 1.0000
10.000 1.0273 0.01899 0.01405 0.0122 0.0094 1.0000
10.250 1.0463 0.01975 0.01487 0.0133 0.0091 1.0000
10.500 1.0630 0.02074 0.01595 0.0147 0.0088 1.0000
10.750 1.0722 0.02267 0.01805 0.0168 0.0084 1.0000
11.000 1.0832 0.02427 0.01985 0.0188 0.0081 1.0000
11.250 1.0978 0.02527 0.02099 0.0203 0.0080 1.0000
11.500 1.1085 0.02660 0.02247 0.0221 0.0079 1.0000
11.750 1.1169 0.02800 0.02401 0.0242 0.0077 1.0000
12.000 1.1198 0.02935 0.02551 0.0271 0.0076 1.0000
12.250 1.1174 0.03101 0.02732 0.0302 0.0075 1.0000
12.500 1.1138 0.03290 0.02936 0.0326 0.0074 1.0000
12.750 1.1054 0.03549 0.03214 0.0343 0.0073 1.0000
13.000 1.1028 0.03780 0.03458 0.0348 0.0073 1.0000
13.250 1.0900 0.04164 0.03861 0.0344 0.0072 1.0000
13.500 1.0730 0.04663 0.04381 0.0324 0.0072 1.0000
13.750 1.0578 0.05202 0.04937 0.0294 0.0073 1.0000
14.000 1.0363 0.05907 0.05661 0.0249 0.0073 1.0000
14.250 1.0126 0.06717 0.06489 0.0194 0.0073 1.0000
14.500 0.9905 0.07560 0.07345 0.0137 0.0073 1.0000
14.750 0.9585 0.08680 0.08481 0.0065 0.0074 1.0000
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