RAF 69 AIRFOIL (raf69-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 69 AIRFOIL (raf69-il) Reynolds number: 50,000 Max Cl/Cd: 18.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf69-il-50000-n5.txt Download as CSV file: xf-raf69-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 69 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4987 0.09512 0.08615 -0.0606 1.0000 0.1729
-12.500 -0.6753 0.06609 0.05698 -0.0709 1.0000 0.1879
-12.250 -0.5883 0.07432 0.06540 -0.0661 1.0000 0.1906
-12.000 -0.5823 0.07317 0.06428 -0.0649 1.0000 0.1946
-11.750 -0.7196 0.05795 0.04888 -0.0667 1.0000 0.1997
-11.500 -0.7839 0.05316 0.04395 -0.0623 1.0000 0.2018
-11.250 -0.8367 0.05046 0.04112 -0.0559 1.0000 0.2034
-11.000 -0.8365 0.05011 0.04088 -0.0525 1.0000 0.2067
-10.750 -0.8516 0.04945 0.04026 -0.0477 1.0000 0.2097
-10.500 -0.8801 0.04850 0.03928 -0.0414 1.0000 0.2122
-10.250 -0.8953 0.04702 0.03763 -0.0377 0.9950 0.2168
-10.000 -0.8775 0.04573 0.03621 -0.0385 0.9860 0.2236
-9.750 -0.8536 0.04488 0.03530 -0.0396 0.9783 0.2311
-9.500 -0.8430 0.04335 0.03354 -0.0394 0.9683 0.2386
-9.250 -0.8152 0.04292 0.03315 -0.0403 0.9608 0.2460
-9.000 -0.8030 0.04145 0.03137 -0.0401 0.9520 0.2548
-8.750 -0.7760 0.04119 0.03123 -0.0404 0.9441 0.2617
-8.500 -0.7573 0.04005 0.02985 -0.0407 0.9364 0.2711
-8.250 -0.7356 0.03967 0.02953 -0.0402 0.9279 0.2781
-8.000 -0.7131 0.03886 0.02856 -0.0405 0.9208 0.2874
-7.750 -0.6936 0.03836 0.02805 -0.0398 0.9127 0.2951
-7.500 -0.6710 0.03779 0.02739 -0.0397 0.9052 0.3041
-7.250 -0.6403 0.03719 0.02673 -0.0409 0.9000 0.3136
-7.000 -0.6296 0.03684 0.02635 -0.0386 0.8901 0.3214
-6.750 -0.6013 0.03624 0.02566 -0.0393 0.8842 0.3313
-6.500 -0.5822 0.03593 0.02533 -0.0383 0.8764 0.3402
-6.250 -0.5634 0.03547 0.02479 -0.0373 0.8685 0.3495
-6.000 -0.5292 0.03505 0.02435 -0.0387 0.8636 0.3607
-5.750 -0.5183 0.03481 0.02408 -0.0362 0.8542 0.3694
-5.500 -0.4936 0.03449 0.02372 -0.0360 0.8474 0.3802
-5.250 -0.4571 0.03411 0.02334 -0.0376 0.8429 0.3925
-5.000 -0.4539 0.03395 0.02311 -0.0338 0.8322 0.4024
-4.750 -0.4231 0.03373 0.02294 -0.0343 0.8262 0.4142
-4.500 -0.3866 0.03333 0.02251 -0.0358 0.8219 0.4285
-4.250 -0.3860 0.03338 0.02254 -0.0315 0.8103 0.4388
-4.000 -0.3531 0.03313 0.02232 -0.0322 0.8049 0.4529
-3.750 -0.3369 0.03302 0.02219 -0.0304 0.7967 0.4661
-3.500 -0.3194 0.03292 0.02207 -0.0287 0.7883 0.4803
-3.250 -0.2833 0.03270 0.02189 -0.0297 0.7836 0.4964
-3.000 -0.2762 0.03285 0.02208 -0.0264 0.7733 0.5087
-2.750 -0.2500 0.03271 0.02192 -0.0259 0.7667 0.5252
-2.500 -0.2133 0.03245 0.02165 -0.0270 0.7625 0.5435
-2.250 -0.2123 0.03283 0.02210 -0.0226 0.7507 0.5556
-2.000 -0.1792 0.03272 0.02201 -0.0231 0.7454 0.5727
-1.750 -0.1648 0.03289 0.02219 -0.0207 0.7367 0.5880
-1.500 -0.1461 0.03296 0.02227 -0.0190 0.7286 0.6046
-1.250 -0.1105 0.03282 0.02213 -0.0197 0.7242 0.6232
-1.000 -0.1072 0.03331 0.02268 -0.0157 0.7129 0.6366
-0.750 -0.0756 0.03331 0.02270 -0.0157 0.7070 0.6536
-0.500 -0.0356 0.03317 0.02255 -0.0169 0.7033 0.6713
-0.250 -0.0440 0.03378 0.02319 -0.0114 0.6903 0.6859
0.000 -0.0081 0.03365 0.02305 -0.0120 0.6856 0.7039
0.250 -0.0079 0.03419 0.02361 -0.0077 0.6746 0.7195
0.500 0.0221 0.03424 0.02368 -0.0074 0.6684 0.7357
0.750 0.0650 0.03404 0.02346 -0.0090 0.6647 0.7524
1.000 0.0538 0.03479 0.02426 -0.0033 0.6517 0.7683
1.250 0.0916 0.03463 0.02408 -0.0041 0.6471 0.7852
1.750 0.1220 0.03529 0.02478 -0.0001 0.6299 0.8195
2.000 0.1790 0.03508 0.02457 -0.0039 0.6264 0.8327
2.250 0.1787 0.03617 0.02573 -0.0006 0.6140 0.8493
2.500 0.2277 0.03600 0.02553 -0.0034 0.6092 0.8634
2.750 0.2876 0.03567 0.02517 -0.0079 0.6056 0.8756
3.000 0.2950 0.03696 0.02655 -0.0063 0.5926 0.8911
3.250 0.3566 0.03654 0.02609 -0.0111 0.5887 0.9017
3.500 0.3694 0.03774 0.02735 -0.0105 0.5766 0.9177
3.750 0.4357 0.03739 0.02698 -0.0165 0.5715 0.9250
4.250 0.5077 0.03807 0.02770 -0.0208 0.5543 0.9506
4.500 0.5801 0.03715 0.02674 -0.0272 0.5500 0.9565
4.750 0.5898 0.03850 0.02818 -0.0268 0.5372 0.9734
5.000 0.6550 0.03758 0.02723 -0.0322 0.5321 0.9809
5.250 0.6732 0.03875 0.02848 -0.0332 0.5201 0.9969
5.500 0.7139 0.03808 0.02778 -0.0350 0.5143 1.0000
5.750 0.6382 0.04010 0.02977 -0.0219 0.5033 1.0000
6.000 0.6461 0.03993 0.02955 -0.0188 0.4971 1.0000
6.500 0.6210 0.04186 0.03136 -0.0092 0.4795 1.0000
6.750 0.6619 0.04072 0.03015 -0.0095 0.4758 1.0000
7.000 0.6174 0.04401 0.03342 -0.0030 0.4619 1.0000
7.250 0.6564 0.04287 0.03223 -0.0028 0.4581 1.0000
7.750 0.6585 0.04526 0.03457 0.0023 0.4402 1.0000
8.250 0.6645 0.04787 0.03717 0.0065 0.4223 1.0000
8.500 0.7123 0.04605 0.03531 0.0065 0.4194 1.0000
8.750 0.6706 0.05089 0.04019 0.0101 0.4043 1.0000
9.000 0.7170 0.04895 0.03821 0.0104 0.4013 1.0000
9.250 0.6780 0.05409 0.04339 0.0131 0.3862 1.0000
9.500 0.7213 0.05225 0.04154 0.0137 0.3832 1.0000
9.750 0.6825 0.05790 0.04723 0.0155 0.3681 1.0000
10.000 0.7254 0.05587 0.04519 0.0164 0.3651 1.0000
10.500 0.7269 0.06008 0.04945 0.0186 0.3472 1.0000
11.000 0.7268 0.06480 0.05421 0.0202 0.3294 1.0000
11.500 0.7240 0.07018 0.05964 0.0212 0.3120 1.0000
12.000 0.7188 0.07623 0.06576 0.0217 0.2949 1.0000
12.500 0.7099 0.08325 0.07285 0.0215 0.2782 1.0000
13.000 0.6970 0.09141 0.08109 0.0205 0.2620 1.0000
13.250 0.7289 0.08978 0.07948 0.0218 0.2600 1.0000
13.750 0.7085 0.09952 0.08930 0.0199 0.2442 1.0000
14.250 0.6852 0.11029 0.10014 0.0170 0.2292 1.0000
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