FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 500,000 Max Cl/Cd: 70.97 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63143-il-500000.txt Download as CSV file: xf-fx63143-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-143 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3811 0.08955 0.08745 -0.0414 1.0000 0.0179
-9.750 -0.3879 0.08382 0.08176 -0.0445 1.0000 0.0181
-9.500 -0.3998 0.07641 0.07439 -0.0495 1.0000 0.0182
-9.250 -0.4167 0.06885 0.06683 -0.0560 1.0000 0.0181
-9.000 -0.4328 0.06218 0.06007 -0.0614 0.9955 0.0181
-8.750 -0.4557 0.05194 0.04929 -0.0680 0.9366 0.0184
-8.500 -0.4169 0.04276 0.03944 -0.0811 0.8957 0.0186
-8.250 -0.3950 0.03972 0.03604 -0.0833 0.8364 0.0187
-8.000 -0.3900 0.03760 0.03363 -0.0810 0.8007 0.0188
-7.750 -0.3835 0.03568 0.03144 -0.0787 0.7735 0.0189
-7.500 -0.3759 0.03354 0.02902 -0.0763 0.7519 0.0191
-7.250 -0.3666 0.03133 0.02651 -0.0740 0.7343 0.0193
-7.000 -0.3550 0.02909 0.02396 -0.0718 0.7202 0.0196
-6.750 -0.3411 0.02702 0.02156 -0.0697 0.7068 0.0199
-6.500 -0.3257 0.02494 0.01909 -0.0676 0.6924 0.0202
-6.250 -0.3065 0.02026 0.01364 -0.0645 0.6829 0.0132
-6.000 -0.2840 0.01845 0.01158 -0.0634 0.6720 0.0123
-5.750 -0.2607 0.01673 0.00948 -0.0621 0.6604 0.0114
-5.500 -0.2372 0.01574 0.00842 -0.0614 0.6501 0.0112
-5.250 -0.2144 0.01498 0.00757 -0.0604 0.6404 0.0110
-5.000 -0.1919 0.01424 0.00677 -0.0595 0.6313 0.0109
-4.750 -0.1696 0.01365 0.00611 -0.0585 0.6232 0.0108
-4.500 -0.1465 0.01314 0.00554 -0.0577 0.6156 0.0109
-4.250 -0.1233 0.01275 0.00506 -0.0568 0.6076 0.0111
-3.750 -0.0741 0.01215 0.00433 -0.0557 0.5916 0.0124
-3.500 -0.0479 0.01194 0.00406 -0.0554 0.5846 0.0134
-3.250 -0.0220 0.01180 0.00384 -0.0550 0.5763 0.0139
-3.000 0.0040 0.01165 0.00364 -0.0547 0.5668 0.0145
-2.750 0.0299 0.01158 0.00348 -0.0544 0.5575 0.0152
-2.500 0.0566 0.01156 0.00340 -0.0542 0.5480 0.0159
-2.250 0.0819 0.01139 0.00316 -0.0538 0.5404 0.0173
-2.000 0.1087 0.01130 0.00304 -0.0537 0.5339 0.0181
-1.750 0.1350 0.01121 0.00290 -0.0535 0.5272 0.0187
-1.500 0.1613 0.01103 0.00267 -0.0533 0.5208 0.0209
-1.250 0.1881 0.01092 0.00254 -0.0532 0.5142 0.0217
-0.750 0.2422 0.01081 0.00237 -0.0531 0.5019 0.0223
-0.500 0.2691 0.01076 0.00228 -0.0530 0.4946 0.0234
-0.250 0.2960 0.01074 0.00223 -0.0530 0.4864 0.0238
0.000 0.3229 0.01073 0.00220 -0.0529 0.4780 0.0247
0.250 0.3498 0.01071 0.00218 -0.0528 0.4705 0.0313
0.500 0.3770 0.01072 0.00218 -0.0528 0.4617 0.0342
0.750 0.4039 0.01072 0.00216 -0.0528 0.4540 0.0398
1.000 0.4310 0.01068 0.00214 -0.0528 0.4441 0.0640
1.250 0.4579 0.01071 0.00215 -0.0527 0.4345 0.0678
1.500 0.4846 0.01076 0.00216 -0.0527 0.4250 0.0696
1.750 0.5113 0.01081 0.00219 -0.0526 0.4151 0.0720
2.000 0.5377 0.01087 0.00222 -0.0525 0.4062 0.0790
2.250 0.5647 0.01091 0.00228 -0.0525 0.3960 0.0996
2.500 0.5914 0.01098 0.00234 -0.0525 0.3845 0.1072
2.750 0.6173 0.01099 0.00241 -0.0524 0.3669 0.1611
3.000 0.6432 0.01062 0.00249 -0.0527 0.3531 0.3686
3.250 0.6675 0.00951 0.00279 -0.0529 0.3427 0.8029
3.500 0.6866 0.00969 0.00309 -0.0509 0.3333 0.8466
3.750 0.7067 0.00999 0.00338 -0.0492 0.3164 0.8717
4.000 0.7275 0.01043 0.00374 -0.0477 0.2956 0.8931
4.250 0.7425 0.01072 0.00403 -0.0448 0.2873 0.9035
4.500 0.7644 0.01097 0.00426 -0.0436 0.2805 0.9117
4.750 0.7790 0.01116 0.00448 -0.0406 0.2756 0.9192
5.000 0.8026 0.01136 0.00469 -0.0399 0.2661 0.9265
5.250 0.8153 0.01154 0.00486 -0.0366 0.2489 0.9319
5.500 0.8316 0.01180 0.00508 -0.0344 0.2390 0.9388
5.750 0.8401 0.01191 0.00519 -0.0302 0.2334 0.9482
6.000 0.8531 0.01211 0.00538 -0.0272 0.2235 0.9571
6.250 0.8651 0.01219 0.00547 -0.0240 0.2148 0.9636
6.500 0.8768 0.01262 0.00577 -0.0213 0.1831 0.9698
6.750 0.8956 0.01285 0.00598 -0.0199 0.1736 0.9739
7.000 0.9168 0.01309 0.00623 -0.0190 0.1654 0.9783
7.250 0.9341 0.01349 0.00657 -0.0176 0.1386 0.9827
7.500 0.9672 0.01405 0.00707 -0.0195 0.1291 0.9887
7.750 1.0105 0.01446 0.00752 -0.0233 0.1231 0.9935
8.250 1.0721 0.01569 0.00867 -0.0267 0.0923 1.0000
8.500 1.0640 0.01590 0.00890 -0.0203 0.0903 1.0000
8.750 1.0691 0.01622 0.00927 -0.0167 0.0881 1.0000
9.000 1.0847 0.01659 0.00971 -0.0152 0.0864 1.0000
9.250 1.1031 0.01699 0.01019 -0.0143 0.0841 1.0000
9.500 1.1196 0.01757 0.01083 -0.0134 0.0797 1.0000
9.750 1.1389 0.01805 0.01139 -0.0129 0.0744 1.0000
10.000 1.1531 0.01886 0.01218 -0.0120 0.0643 1.0000
10.250 1.1632 0.01998 0.01329 -0.0109 0.0597 1.0000
10.500 1.1709 0.02137 0.01472 -0.0099 0.0567 1.0000
10.750 1.1807 0.02271 0.01615 -0.0093 0.0532 1.0000
11.000 1.1897 0.02422 0.01778 -0.0089 0.0493 1.0000
11.250 1.2073 0.02511 0.01874 -0.0090 0.0367 1.0000
11.500 1.2142 0.02692 0.02046 -0.0087 0.0295 1.0000
11.750 1.2198 0.02892 0.02251 -0.0085 0.0271 1.0000
12.000 1.2240 0.03110 0.02475 -0.0084 0.0253 1.0000
12.250 1.2267 0.03349 0.02724 -0.0083 0.0238 1.0000
12.500 1.2267 0.03618 0.03004 -0.0082 0.0228 1.0000
12.750 1.2327 0.03833 0.03227 -0.0084 0.0223 1.0000
13.000 1.2381 0.04054 0.03458 -0.0086 0.0215 1.0000
13.250 1.2412 0.04302 0.03716 -0.0088 0.0211 1.0000
13.500 1.2442 0.04554 0.03977 -0.0091 0.0203 1.0000
13.750 1.2462 0.04823 0.04255 -0.0094 0.0198 1.0000
14.000 1.2476 0.05104 0.04545 -0.0099 0.0192 1.0000
14.250 1.2487 0.05397 0.04847 -0.0104 0.0186 1.0000
14.500 1.2484 0.05713 0.05171 -0.0111 0.0182 1.0000
14.750 1.2468 0.06051 0.05518 -0.0118 0.0176 1.0000
15.000 1.2435 0.06422 0.05897 -0.0127 0.0171 1.0000
15.250 1.2369 0.06836 0.06323 -0.0137 0.0165 1.0000
15.500 1.2347 0.07203 0.06699 -0.0147 0.0162 1.0000
15.750 1.2389 0.07500 0.07006 -0.0157 0.0159 1.0000
16.000 1.2420 0.07813 0.07329 -0.0168 0.0154 1.0000
16.250 1.2444 0.08142 0.07668 -0.0180 0.0148 1.0000
16.500 1.2457 0.08490 0.08025 -0.0193 0.0141 1.0000
16.750 1.2461 0.08858 0.08401 -0.0207 0.0133 1.0000
17.000 1.2439 0.09268 0.08818 -0.0223 0.0127 1.0000
17.250 1.2363 0.09749 0.09306 -0.0240 0.0118 1.0000
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