FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 500,000 Max Cl/Cd: 74.87 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx68h120-il-500000.txt Download as CSV file: xf-fx68h120-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 68-H-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5066 0.09440 0.09245 -0.0229 1.0000 0.0178
-11.000 -0.4945 0.09329 0.09134 -0.0240 1.0000 0.0185
-10.500 -0.6665 0.04226 0.03944 -0.0646 0.9678 0.0108
-10.250 -0.6876 0.03938 0.03630 -0.0615 0.9498 0.0107
-10.000 -0.7036 0.03669 0.03335 -0.0576 0.9390 0.0106
-9.500 -0.7108 0.03124 0.02728 -0.0517 0.9248 0.0106
-9.250 -0.7041 0.02919 0.02493 -0.0493 0.9198 0.0107
-9.000 -0.6927 0.02740 0.02287 -0.0474 0.9158 0.0109
-8.750 -0.6773 0.02573 0.02096 -0.0459 0.9115 0.0110
-8.500 -0.6611 0.02440 0.01939 -0.0443 0.9076 0.0113
-8.250 -0.6484 0.02216 0.01687 -0.0421 0.9041 0.0114
-8.000 -0.6322 0.02003 0.01452 -0.0406 0.9007 0.0118
-7.750 -0.6129 0.01865 0.01301 -0.0394 0.8972 0.0123
-7.500 -0.5922 0.01769 0.01193 -0.0383 0.8941 0.0128
-7.250 -0.5699 0.01714 0.01132 -0.0373 0.8913 0.0138
-7.000 -0.5473 0.01646 0.01054 -0.0364 0.8886 0.0145
-6.750 -0.5232 0.01570 0.00968 -0.0357 0.8855 0.0152
-6.500 -0.4991 0.01507 0.00896 -0.0350 0.8825 0.0160
-6.250 -0.4748 0.01458 0.00837 -0.0342 0.8797 0.0166
-6.000 -0.4537 0.01364 0.00728 -0.0328 0.8771 0.0185
-5.750 -0.4293 0.01312 0.00671 -0.0320 0.8748 0.0211
-5.500 -0.4033 0.01258 0.00610 -0.0316 0.8718 0.0276
-5.250 -0.3817 0.01156 0.00547 -0.0307 0.8685 0.0880
-5.000 -0.3563 0.01134 0.00530 -0.0300 0.8648 0.1121
-4.750 -0.3312 0.01120 0.00512 -0.0292 0.8599 0.1237
-4.500 -0.3050 0.01104 0.00493 -0.0286 0.8529 0.1334
-4.250 -0.2800 0.01085 0.00471 -0.0277 0.8483 0.1414
-4.000 -0.2526 0.01076 0.00459 -0.0275 0.8429 0.1522
-3.750 -0.2254 0.01068 0.00449 -0.0271 0.8379 0.1629
-3.500 -0.1999 0.01044 0.00425 -0.0264 0.8341 0.1707
-3.250 -0.1722 0.01034 0.00410 -0.0263 0.8295 0.1772
-3.000 -0.1459 0.01008 0.00386 -0.0258 0.8246 0.1843
-2.750 -0.1194 0.00991 0.00364 -0.0253 0.8203 0.1910
-2.500 -0.0927 0.00969 0.00347 -0.0250 0.8150 0.1999
-2.250 -0.0658 0.00950 0.00328 -0.0246 0.8097 0.2097
-2.000 -0.0396 0.00929 0.00306 -0.0240 0.8049 0.2226
-1.750 -0.0129 0.00903 0.00291 -0.0237 0.7973 0.2428
-1.500 0.0126 0.00873 0.00270 -0.0230 0.7904 0.2783
-1.250 0.0378 0.00834 0.00256 -0.0224 0.7817 0.3412
-1.000 0.0614 0.00788 0.00241 -0.0215 0.7738 0.4338
-0.750 0.0835 0.00738 0.00228 -0.0203 0.7648 0.5452
-0.500 0.1028 0.00682 0.00220 -0.0184 0.7548 0.6768
-0.250 0.1248 0.00623 0.00219 -0.0165 0.7439 0.8381
0.000 0.1844 0.00621 0.00230 -0.0226 0.7268 0.9246
0.250 0.2259 0.00632 0.00231 -0.0251 0.7069 0.9459
0.500 0.2622 0.00647 0.00234 -0.0266 0.6774 0.9590
0.750 0.2968 0.00675 0.00236 -0.0277 0.6204 0.9700
1.000 0.3401 0.00730 0.00246 -0.0311 0.5340 0.9760
1.250 0.3748 0.00776 0.00263 -0.0327 0.4820 0.9832
1.500 0.4175 0.00808 0.00272 -0.0361 0.4420 0.9871
1.750 0.4584 0.00837 0.00283 -0.0390 0.4095 0.9923
2.000 0.4997 0.00859 0.00289 -0.0421 0.3815 0.9965
2.250 0.5406 0.00878 0.00293 -0.0451 0.3560 1.0000
2.500 0.5645 0.00898 0.00301 -0.0445 0.3367 1.0000
2.750 0.5884 0.00915 0.00310 -0.0439 0.3191 1.0000
3.000 0.6123 0.00934 0.00320 -0.0433 0.3028 1.0000
3.250 0.6361 0.00953 0.00330 -0.0426 0.2878 1.0000
3.500 0.6598 0.00972 0.00344 -0.0419 0.2737 1.0000
3.750 0.6834 0.00993 0.00357 -0.0412 0.2605 1.0000
4.000 0.7067 0.01015 0.00373 -0.0405 0.2486 1.0000
4.500 0.7530 0.01061 0.00409 -0.0390 0.2282 1.0000
4.750 0.7758 0.01085 0.00429 -0.0381 0.2201 1.0000
5.000 0.7985 0.01110 0.00450 -0.0372 0.2125 1.0000
5.250 0.8211 0.01134 0.00472 -0.0363 0.2057 1.0000
5.500 0.8433 0.01160 0.00493 -0.0354 0.1973 1.0000
5.750 0.8661 0.01180 0.00515 -0.0346 0.1904 1.0000
6.000 0.8879 0.01208 0.00538 -0.0336 0.1837 1.0000
6.250 0.9104 0.01228 0.00558 -0.0327 0.1764 1.0000
6.500 0.9319 0.01256 0.00583 -0.0316 0.1696 1.0000
6.750 0.9543 0.01275 0.00603 -0.0307 0.1620 1.0000
7.000 0.9756 0.01303 0.00623 -0.0297 0.1459 1.0000
7.250 0.9940 0.01356 0.00652 -0.0283 0.1152 1.0000
7.500 0.9944 0.01559 0.00795 -0.0244 0.0174 1.0000
7.750 1.0124 0.01612 0.00854 -0.0227 0.0130 1.0000
8.000 1.0306 0.01658 0.00909 -0.0211 0.0116 1.0000
8.250 1.0476 0.01714 0.00975 -0.0193 0.0106 1.0000
8.500 1.0630 0.01780 0.01052 -0.0173 0.0098 1.0000
8.750 1.0749 0.01870 0.01156 -0.0148 0.0091 1.0000
9.000 1.0840 0.01973 0.01274 -0.0120 0.0088 1.0000
9.250 1.0881 0.02079 0.01392 -0.0084 0.0085 1.0000
9.500 1.0949 0.02154 0.01475 -0.0053 0.0083 1.0000
9.750 1.0988 0.02257 0.01587 -0.0021 0.0083 1.0000
10.000 1.1020 0.02376 0.01716 0.0009 0.0083 1.0000
10.250 1.1050 0.02507 0.01857 0.0036 0.0082 1.0000
10.500 1.1072 0.02653 0.02013 0.0061 0.0081 1.0000
10.750 1.1068 0.02828 0.02198 0.0084 0.0082 1.0000
11.000 1.1055 0.03022 0.02402 0.0106 0.0082 1.0000
11.250 1.1037 0.03233 0.02622 0.0124 0.0082 1.0000
11.500 1.1013 0.03465 0.02862 0.0139 0.0083 1.0000
11.750 1.0957 0.03740 0.03144 0.0154 0.0084 1.0000
12.000 1.0904 0.04033 0.03440 0.0170 0.0087 1.0000
12.250 1.0964 0.04220 0.03636 0.0175 0.0088 1.0000
12.500 1.1024 0.04417 0.03842 0.0178 0.0089 1.0000
12.750 1.1072 0.04636 0.04069 0.0180 0.0091 1.0000
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