FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 100,000 Max Cl/Cd: 40.05 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h60-il-100000-n5.txt Download as CSV file: xf-fx66h60-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-60
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6220 0.10988 0.10531 0.0249 1.0000 0.0306
-8.250 -0.6222 0.10606 0.10153 0.0216 1.0000 0.0307
-8.000 -0.6208 0.10234 0.09782 0.0193 1.0000 0.0307
-7.750 -0.6163 0.09840 0.09386 0.0170 1.0000 0.0308
-7.500 -0.6107 0.09441 0.08983 0.0149 1.0000 0.0308
-7.250 -0.6088 0.08757 0.08309 0.0148 1.0000 0.0315
-7.000 -0.6030 0.08280 0.07835 0.0151 1.0000 0.0323
-6.750 -0.5959 0.07867 0.07422 0.0146 1.0000 0.0331
-6.500 -0.5874 0.07469 0.07021 0.0134 1.0000 0.0339
-6.250 -0.5774 0.07068 0.06614 0.0122 1.0000 0.0348
-6.000 -0.5656 0.06675 0.06212 0.0109 1.0000 0.0359
-5.750 -0.5519 0.06282 0.05809 0.0098 1.0000 0.0371
-5.500 -0.5362 0.05897 0.05408 0.0089 1.0000 0.0386
-5.250 -0.5093 0.05775 0.05220 0.0078 1.0000 0.0436
-4.750 -0.4770 0.04819 0.04239 0.0078 1.0000 0.0448
-4.500 -0.4625 0.04472 0.03904 0.0079 1.0000 0.0512
-4.000 -0.4094 0.03689 0.03027 0.0103 1.0000 0.0295
-3.750 -0.3879 0.03336 0.02650 0.0109 1.0000 0.0275
-3.500 -0.3636 0.03034 0.02304 0.0119 1.0000 0.0259
-3.250 -0.3380 0.02763 0.01995 0.0129 1.0000 0.0247
-3.000 -0.3116 0.02520 0.01713 0.0139 1.0000 0.0237
-2.750 -0.2845 0.02301 0.01456 0.0149 1.0000 0.0229
-2.500 -0.2571 0.02109 0.01232 0.0158 1.0000 0.0225
-2.250 -0.2297 0.01941 0.01042 0.0165 1.0000 0.0224
-2.000 -0.2027 0.01795 0.00883 0.0172 1.0000 0.0228
-1.750 -0.1766 0.01668 0.00752 0.0180 1.0000 0.0236
-1.500 -0.1331 0.01548 0.00612 0.0151 0.8532 0.0265
-1.250 -0.1032 0.01502 0.00524 0.0153 0.7603 0.0364
-1.000 -0.0790 0.01460 0.00443 0.0168 0.7018 0.0455
-0.750 0.0272 0.01166 0.00393 0.0035 0.6270 1.0000
-0.500 0.0512 0.01177 0.00365 0.0043 0.5899 1.0000
-0.250 0.0753 0.01187 0.00340 0.0051 0.5582 1.0000
0.250 0.1238 0.01208 0.00311 0.0066 0.5076 1.0000
0.500 0.1473 0.01221 0.00302 0.0074 0.4869 1.0000
0.750 0.1709 0.01234 0.00298 0.0083 0.4681 1.0000
1.000 0.1949 0.01248 0.00297 0.0090 0.4512 1.0000
1.250 0.2190 0.01262 0.00297 0.0097 0.4360 1.0000
1.500 0.2431 0.01278 0.00301 0.0104 0.4220 1.0000
1.750 0.2670 0.01295 0.00308 0.0111 0.4090 1.0000
2.000 0.2909 0.01312 0.00319 0.0119 0.3969 1.0000
2.250 0.3148 0.01331 0.00332 0.0126 0.3858 1.0000
2.500 0.3387 0.01352 0.00352 0.0133 0.3758 1.0000
2.750 0.3624 0.01375 0.00369 0.0141 0.3663 1.0000
3.000 0.3865 0.01397 0.00392 0.0148 0.3564 1.0000
3.250 0.4106 0.01422 0.00417 0.0155 0.3479 1.0000
3.500 0.4345 0.01449 0.00444 0.0162 0.3402 1.0000
3.750 0.4588 0.01476 0.00478 0.0169 0.3317 1.0000
4.000 0.4828 0.01506 0.00520 0.0176 0.3247 1.0000
4.250 0.5071 0.01537 0.00563 0.0182 0.3172 1.0000
4.500 0.5313 0.01571 0.00603 0.0189 0.3110 1.0000
4.750 0.5557 0.01606 0.00653 0.0195 0.3036 1.0000
5.000 0.5800 0.01644 0.00702 0.0201 0.2977 1.0000
5.250 0.6046 0.01684 0.00765 0.0207 0.2910 1.0000
5.500 0.6290 0.01726 0.00820 0.0214 0.2854 1.0000
5.750 0.6530 0.01728 0.00862 0.0221 0.2662 1.0000
6.000 0.6765 0.01689 0.00833 0.0228 0.2169 1.0000
6.250 0.6926 0.01931 0.00967 0.0231 0.0393 1.0000
6.500 0.7133 0.02112 0.01170 0.0239 0.0278 1.0000
6.750 0.7342 0.02268 0.01362 0.0246 0.0237 1.0000
7.000 0.7516 0.02470 0.01588 0.0252 0.0193 1.0000
7.250 0.7707 0.02620 0.01760 0.0260 0.0166 1.0000
7.500 0.7886 0.02795 0.01953 0.0271 0.0156 1.0000
7.750 0.8064 0.02994 0.02169 0.0283 0.0149 1.0000
8.000 0.8244 0.03215 0.02421 0.0294 0.0144 1.0000
8.250 0.8416 0.03477 0.02711 0.0304 0.0140 1.0000
8.500 0.8569 0.03772 0.03040 0.0312 0.0137 1.0000
8.750 0.8692 0.04098 0.03406 0.0318 0.0135 1.0000
9.000 0.8771 0.04459 0.03808 0.0320 0.0135 1.0000
9.250 0.8798 0.04845 0.04235 0.0319 0.0134 1.0000
9.500 0.8770 0.05244 0.04669 0.0311 0.0135 1.0000
9.750 0.8675 0.05654 0.05105 0.0297 0.0136 1.0000
10.000 0.8536 0.06115 0.05582 0.0260 0.0137 1.0000
10.250 0.8409 0.06673 0.06155 0.0209 0.0138 1.0000
10.500 0.8258 0.07349 0.06843 0.0151 0.0139 1.0000
10.750 0.8114 0.08053 0.07555 0.0095 0.0141 1.0000
11.000 0.7970 0.08803 0.08310 0.0042 0.0143 1.0000
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Polar data table (+)
Polar graphs
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