Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf) Reynolds number: 50,000 Max Cl/Cd: 25.64 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk0015-jf-50000-n5.txt Download as CSV file: xf-joukowsk0015-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=15%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7070 0.12435 0.11594 0.0146 1.0000 0.1167
-13.000 -0.7106 0.11897 0.11055 0.0120 1.0000 0.1201
-12.750 -0.8741 0.08159 0.07299 -0.0119 1.0000 0.1250
-12.500 -0.7693 0.09735 0.08893 0.0001 1.0000 0.1281
-12.250 -0.8314 0.08153 0.07304 -0.0095 1.0000 0.1322
-12.000 -0.9213 0.06454 0.05569 -0.0203 1.0000 0.1334
-11.750 -0.9568 0.05755 0.04842 -0.0235 1.0000 0.1355
-11.500 -0.9848 0.05237 0.04290 -0.0247 1.0000 0.1380
-11.250 -0.9622 0.05175 0.04243 -0.0239 1.0000 0.1424
-11.000 -0.9645 0.04923 0.03980 -0.0235 1.0000 0.1465
-10.750 -0.9761 0.04623 0.03651 -0.0224 1.0000 0.1507
-10.500 -0.9612 0.04504 0.03540 -0.0215 1.0000 0.1557
-10.250 -0.9536 0.04329 0.03355 -0.0207 1.0000 0.1613
-10.000 -0.9469 0.04135 0.03144 -0.0197 1.0000 0.1674
-9.750 -0.9308 0.04026 0.03039 -0.0189 1.0000 0.1739
-9.500 -0.9220 0.03843 0.02833 -0.0180 1.0000 0.1814
-9.250 -0.9031 0.03756 0.02757 -0.0172 1.0000 0.1886
-9.000 -0.8902 0.03603 0.02585 -0.0164 1.0000 0.1972
-8.750 -0.8709 0.03518 0.02509 -0.0156 1.0000 0.2055
-8.500 -0.8544 0.03398 0.02380 -0.0148 1.0000 0.2149
-8.250 -0.8359 0.03304 0.02284 -0.0140 1.0000 0.2248
-8.000 -0.8163 0.03217 0.02199 -0.0133 1.0000 0.2347
-7.750 -0.7983 0.03113 0.02084 -0.0125 1.0000 0.2462
-7.500 -0.7771 0.03046 0.02025 -0.0117 1.0000 0.2569
-7.250 -0.7566 0.02971 0.01951 -0.0110 1.0000 0.2684
-7.000 -0.7367 0.02888 0.01862 -0.0103 1.0000 0.2810
-6.750 -0.7154 0.02828 0.01807 -0.0095 1.0000 0.2934
-6.500 -0.6939 0.02771 0.01755 -0.0087 1.0000 0.3055
-6.250 -0.6732 0.02709 0.01693 -0.0079 1.0000 0.3187
-6.000 -0.6533 0.02646 0.01626 -0.0070 1.0000 0.3327
-5.750 -0.6323 0.02608 0.01601 -0.0060 1.0000 0.3449
-5.500 -0.6132 0.02563 0.01561 -0.0048 1.0000 0.3577
-5.250 -0.5966 0.02516 0.01515 -0.0034 1.0000 0.3712
-5.000 -0.5816 0.02482 0.01486 -0.0016 1.0000 0.3838
-4.750 -0.5679 0.02455 0.01467 0.0003 1.0000 0.3956
-4.500 -0.5437 0.02426 0.01440 0.0002 0.9917 0.4102
-4.250 -0.5006 0.02406 0.01420 -0.0030 0.9730 0.4283
-4.000 -0.4568 0.02387 0.01401 -0.0062 0.9562 0.4463
-3.750 -0.4147 0.02370 0.01384 -0.0088 0.9391 0.4640
-3.500 -0.3753 0.02354 0.01367 -0.0109 0.9218 0.4814
-3.250 -0.3390 0.02346 0.01359 -0.0121 0.9038 0.4973
-3.000 -0.3059 0.02340 0.01356 -0.0126 0.8857 0.5121
-2.750 -0.2755 0.02333 0.01348 -0.0125 0.8676 0.5270
-2.500 -0.2473 0.02324 0.01337 -0.0121 0.8499 0.5423
-2.250 -0.2213 0.02315 0.01323 -0.0113 0.8320 0.5579
-2.000 -0.1957 0.02315 0.01326 -0.0101 0.8145 0.5714
-1.750 -0.1707 0.02313 0.01323 -0.0090 0.7973 0.5853
-1.500 -0.1461 0.02308 0.01316 -0.0078 0.7807 0.6003
-1.250 -0.1217 0.02302 0.01305 -0.0067 0.7645 0.6159
-1.000 -0.0967 0.02303 0.01309 -0.0053 0.7492 0.6291
-0.750 -0.0723 0.02300 0.01304 -0.0038 0.7345 0.6433
-0.500 -0.0484 0.02299 0.01302 -0.0027 0.7182 0.6586
-0.250 -0.0244 0.02298 0.01299 -0.0015 0.7026 0.6741
0.000 0.0000 0.02300 0.01304 0.0000 0.6878 0.6878
0.250 0.0244 0.02298 0.01299 0.0015 0.6741 0.7026
0.500 0.0484 0.02299 0.01302 0.0027 0.6586 0.7182
0.750 0.0723 0.02300 0.01304 0.0038 0.6433 0.7345
1.000 0.0967 0.02303 0.01309 0.0053 0.6291 0.7492
1.250 0.1217 0.02302 0.01305 0.0067 0.6159 0.7645
1.500 0.1461 0.02308 0.01316 0.0078 0.6002 0.7807
1.750 0.1707 0.02313 0.01323 0.0090 0.5854 0.7973
2.000 0.1957 0.02315 0.01326 0.0101 0.5714 0.8145
2.250 0.2213 0.02315 0.01323 0.0113 0.5579 0.8320
2.500 0.2474 0.02324 0.01337 0.0121 0.5423 0.8499
2.750 0.2755 0.02332 0.01348 0.0125 0.5270 0.8677
3.000 0.3059 0.02340 0.01356 0.0126 0.5122 0.8857
3.250 0.3390 0.02345 0.01359 0.0121 0.4973 0.9039
3.500 0.3753 0.02354 0.01367 0.0109 0.4814 0.9218
3.750 0.4148 0.02370 0.01384 0.0088 0.4640 0.9391
4.000 0.4569 0.02387 0.01401 0.0062 0.4463 0.9562
4.250 0.5007 0.02406 0.01420 0.0030 0.4282 0.9731
4.500 0.5438 0.02426 0.01439 -0.0002 0.4102 0.9918
4.750 0.5679 0.02455 0.01467 -0.0003 0.3956 1.0000
5.000 0.5816 0.02482 0.01486 0.0016 0.3838 1.0000
5.250 0.5966 0.02516 0.01515 0.0034 0.3712 1.0000
5.500 0.6132 0.02563 0.01561 0.0048 0.3577 1.0000
5.750 0.6323 0.02608 0.01601 0.0060 0.3449 1.0000
6.000 0.6533 0.02646 0.01626 0.0070 0.3327 1.0000
6.250 0.6732 0.02709 0.01693 0.0079 0.3187 1.0000
6.500 0.6939 0.02771 0.01755 0.0087 0.3055 1.0000
6.750 0.7154 0.02828 0.01807 0.0095 0.2933 1.0000
7.000 0.7367 0.02888 0.01862 0.0103 0.2811 1.0000
7.250 0.7566 0.02971 0.01951 0.0110 0.2684 1.0000
7.500 0.7771 0.03046 0.02025 0.0117 0.2569 1.0000
7.750 0.7983 0.03113 0.02084 0.0125 0.2462 1.0000
8.000 0.8163 0.03217 0.02199 0.0132 0.2346 1.0000
8.250 0.8360 0.03304 0.02284 0.0140 0.2248 1.0000
8.500 0.8545 0.03398 0.02380 0.0148 0.2149 1.0000
8.750 0.8711 0.03518 0.02509 0.0156 0.2055 1.0000
9.000 0.8904 0.03603 0.02586 0.0164 0.1972 1.0000
9.250 0.9032 0.03755 0.02757 0.0172 0.1886 1.0000
9.500 0.9222 0.03843 0.02833 0.0180 0.1814 1.0000
9.750 0.9310 0.04026 0.03039 0.0189 0.1738 1.0000
10.000 0.9472 0.04134 0.03143 0.0197 0.1674 1.0000
10.250 0.9539 0.04329 0.03355 0.0206 0.1613 1.0000
10.500 0.9615 0.04502 0.03538 0.0215 0.1556 1.0000
10.750 0.9762 0.04625 0.03652 0.0223 0.1506 1.0000
11.000 0.9649 0.04923 0.03979 0.0234 0.1464 1.0000
11.250 0.9631 0.05172 0.04240 0.0239 0.1423 1.0000
11.500 0.9849 0.05242 0.04293 0.0246 0.1379 1.0000
11.750 0.9570 0.05761 0.04847 0.0234 0.1354 1.0000
12.000 0.9219 0.06457 0.05571 0.0202 0.1333 1.0000
12.250 0.8338 0.08129 0.07279 0.0096 0.1321 1.0000
12.500 0.7736 0.09670 0.08828 0.0002 0.1280 1.0000
12.750 0.8722 0.08208 0.07349 0.0114 0.1250 1.0000
13.000 0.7117 0.11903 0.11061 -0.0122 0.1199 1.0000
13.250 0.7087 0.12430 0.11588 -0.0147 0.1166 1.0000
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