FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.65 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63143-il-1000000-n5.txt Download as CSV file: xf-fx63143-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4671 0.04178 0.03825 -0.0954 0.6364 0.0054
-10.250 -0.4841 0.03866 0.03489 -0.0931 0.6230 0.0053
-10.000 -0.4921 0.03659 0.03266 -0.0903 0.6197 0.0053
-6.500 -0.3468 0.01600 0.00919 -0.0611 0.4881 0.0050
-6.250 -0.3244 0.01516 0.00825 -0.0603 0.4830 0.0048
-6.000 -0.3013 0.01454 0.00752 -0.0595 0.4769 0.0046
-5.750 -0.2776 0.01406 0.00694 -0.0589 0.4692 0.0045
-5.500 -0.2541 0.01363 0.00641 -0.0582 0.4574 0.0043
-5.250 -0.2300 0.01328 0.00597 -0.0576 0.4429 0.0043
-5.000 -0.2067 0.01304 0.00557 -0.0568 0.4172 0.0042
-4.750 -0.1831 0.01282 0.00523 -0.0561 0.3934 0.0041
-4.500 -0.1608 0.01276 0.00495 -0.0552 0.3453 0.0040
-4.250 -0.1398 0.01283 0.00475 -0.0541 0.2772 0.0040
-4.000 -0.1173 0.01282 0.00455 -0.0533 0.2224 0.0039
-3.750 -0.0922 0.01260 0.00428 -0.0529 0.2130 0.0039
-3.500 -0.0684 0.01252 0.00408 -0.0523 0.1724 0.0039
-3.250 -0.0430 0.01232 0.00383 -0.0519 0.1657 0.0039
-3.000 -0.0169 0.01215 0.00362 -0.0517 0.1615 0.0039
-2.750 0.0087 0.01204 0.00344 -0.0514 0.1383 0.0040
-2.500 0.0347 0.01194 0.00329 -0.0511 0.1296 0.0040
-2.250 0.0613 0.01184 0.00315 -0.0510 0.1259 0.0041
-2.000 0.0880 0.01176 0.00303 -0.0508 0.1219 0.0043
-1.750 0.1147 0.01171 0.00295 -0.0507 0.1171 0.0045
-1.500 0.1418 0.01166 0.00287 -0.0507 0.1146 0.0049
-1.250 0.1687 0.01163 0.00282 -0.0506 0.1029 0.0052
-1.000 0.1951 0.01165 0.00278 -0.0505 0.0931 0.0056
-0.750 0.2220 0.01162 0.00271 -0.0504 0.0891 0.0066
-0.500 0.2492 0.01164 0.00272 -0.0504 0.0871 0.0076
-0.250 0.2764 0.01161 0.00270 -0.0504 0.0860 0.0107
0.000 0.3035 0.01163 0.00270 -0.0504 0.0849 0.0114
0.250 0.3306 0.01165 0.00271 -0.0504 0.0834 0.0118
0.500 0.3577 0.01168 0.00273 -0.0504 0.0816 0.0122
0.750 0.3847 0.01172 0.00276 -0.0504 0.0799 0.0130
1.000 0.4117 0.01177 0.00281 -0.0504 0.0778 0.0137
1.250 0.4389 0.01181 0.00284 -0.0504 0.0768 0.0153
1.500 0.4661 0.01184 0.00286 -0.0505 0.0752 0.0176
1.750 0.4928 0.01192 0.00291 -0.0504 0.0613 0.0182
2.000 0.5194 0.01201 0.00297 -0.0504 0.0597 0.0191
2.250 0.5462 0.01209 0.00302 -0.0504 0.0575 0.0200
2.500 0.5731 0.01217 0.00310 -0.0504 0.0566 0.0203
2.750 0.5999 0.01225 0.00318 -0.0503 0.0560 0.0208
3.000 0.6266 0.01234 0.00329 -0.0503 0.0556 0.0222
3.250 0.6533 0.01244 0.00340 -0.0503 0.0554 0.0326
3.500 0.6798 0.01254 0.00352 -0.0503 0.0551 0.0351
3.750 0.7063 0.01265 0.00364 -0.0503 0.0549 0.0374
4.000 0.7327 0.01276 0.00377 -0.0502 0.0548 0.0415
4.250 0.7591 0.01287 0.00392 -0.0502 0.0547 0.0598
4.500 0.7853 0.01300 0.00407 -0.0501 0.0547 0.0659
4.750 0.8113 0.01313 0.00423 -0.0500 0.0547 0.0720
5.250 0.8627 0.01343 0.00462 -0.0498 0.0533 0.1010
5.500 0.8880 0.01360 0.00484 -0.0496 0.0524 0.1098
5.750 0.9135 0.01374 0.00507 -0.0494 0.0519 0.1497
6.000 0.9389 0.01388 0.00530 -0.0493 0.0514 0.1906
6.250 0.9654 0.01389 0.00559 -0.0497 0.0506 0.3206
6.500 1.0053 0.01303 0.00612 -0.0536 0.0491 0.8287
6.750 1.0268 0.01332 0.00651 -0.0526 0.0478 0.8587
7.000 1.0483 0.01363 0.00688 -0.0517 0.0469 0.8711
7.250 1.0717 0.01387 0.00715 -0.0511 0.0464 0.8798
7.500 1.0953 0.01408 0.00739 -0.0506 0.0459 0.8873
7.750 1.1204 0.01431 0.00763 -0.0504 0.0449 0.8928
8.000 1.1420 0.01453 0.00790 -0.0495 0.0435 0.8969
8.250 1.1625 0.01478 0.00820 -0.0484 0.0397 0.9032
8.500 1.1780 0.01541 0.00870 -0.0466 0.0231 0.9087
8.750 1.1927 0.01588 0.00918 -0.0446 0.0175 0.9126
9.000 1.2054 0.01632 0.00965 -0.0423 0.0154 0.9148
9.250 1.2187 0.01677 0.01013 -0.0401 0.0146 0.9173
9.500 1.2306 0.01730 0.01068 -0.0378 0.0134 0.9204
9.750 1.2429 0.01787 0.01128 -0.0357 0.0123 0.9238
10.000 1.2556 0.01848 0.01194 -0.0338 0.0116 0.9264
10.250 1.2624 0.01909 0.01262 -0.0309 0.0111 0.9307
10.500 1.2715 0.01975 0.01334 -0.0286 0.0110 0.9341
10.750 1.2809 0.02051 0.01417 -0.0266 0.0109 0.9373
11.000 1.2904 0.02140 0.01511 -0.0250 0.0108 0.9401
11.250 1.2997 0.02240 0.01617 -0.0235 0.0105 0.9423
11.500 1.3071 0.02349 0.01734 -0.0220 0.0103 0.9445
11.750 1.3142 0.02472 0.01864 -0.0207 0.0101 0.9462
12.000 1.3214 0.02606 0.02005 -0.0196 0.0099 0.9479
12.250 1.3283 0.02753 0.02159 -0.0187 0.0097 0.9496
12.500 1.3346 0.02914 0.02328 -0.0179 0.0095 0.9512
12.750 1.3409 0.03084 0.02504 -0.0173 0.0092 0.9527
13.000 1.3465 0.03268 0.02695 -0.0168 0.0089 0.9542
13.250 1.3521 0.03457 0.02890 -0.0165 0.0087 0.9555
13.500 1.3560 0.03668 0.03107 -0.0162 0.0082 0.9566
13.750 1.3577 0.03888 0.03334 -0.0157 0.0078 0.9587
14.000 1.3587 0.04118 0.03572 -0.0153 0.0075 0.9606
14.250 1.3591 0.04366 0.03828 -0.0150 0.0072 0.9622
14.500 1.3627 0.04591 0.04061 -0.0150 0.0072 0.9638
14.750 1.3681 0.04806 0.04282 -0.0151 0.0070 0.9652
15.000 1.3727 0.05035 0.04518 -0.0153 0.0067 0.9667
15.250 1.3767 0.05279 0.04769 -0.0156 0.0062 0.9682
15.500 1.3792 0.05547 0.05045 -0.0160 0.0058 0.9696
16.000 1.3813 0.06123 0.05629 -0.0170 0.0038 0.9734
16.500 1.3774 0.06811 0.06326 -0.0186 0.0025 0.9779
16.750 1.3780 0.07139 0.06663 -0.0196 0.0024 0.9800
17.000 1.3781 0.07483 0.07015 -0.0208 0.0024 0.9818
17.500 1.3744 0.08245 0.07794 -0.0235 0.0020 0.9923
17.750 1.3697 0.08683 0.08240 -0.0252 0.0017 0.9998
18.000 1.3670 0.09097 0.08662 -0.0268 0.0015 1.0000
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