RAF 89 AIRFOIL (raf89-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 89 AIRFOIL (raf89-il) Reynolds number: 100,000 Max Cl/Cd: 27.35 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf89-il-100000-n5.txt Download as CSV file: xf-raf89-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 89 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.5522 0.12589 0.11872 -0.0631 1.0000 0.1134
-17.500 -0.6506 0.10362 0.09619 -0.0720 1.0000 0.1246
-17.250 -0.6214 0.10530 0.09798 -0.0708 1.0000 0.1259
-17.000 -0.6029 0.10535 0.09810 -0.0703 1.0000 0.1276
-16.750 -0.7041 0.08747 0.07982 -0.0773 1.0000 0.1355
-16.500 -0.6830 0.08787 0.08035 -0.0764 1.0000 0.1376
-16.250 -0.6808 0.08564 0.07815 -0.0767 1.0000 0.1408
-16.000 -0.7225 0.07750 0.06980 -0.0792 1.0000 0.1458
-15.750 -0.7264 0.07469 0.06701 -0.0794 1.0000 0.1490
-15.500 -0.7256 0.07263 0.06500 -0.0793 1.0000 0.1525
-15.250 -0.7460 0.06808 0.06036 -0.0799 1.0000 0.1568
-15.000 -0.7634 0.06421 0.05642 -0.0800 1.0000 0.1608
-14.750 -0.7630 0.06267 0.05496 -0.0791 1.0000 0.1641
-14.500 -0.7766 0.05990 0.05218 -0.0782 1.0000 0.1680
-14.250 -0.8015 0.05666 0.04885 -0.0767 1.0000 0.1719
-13.750 -0.7734 0.05170 0.04388 -0.0818 0.9810 0.1822
-13.500 -0.7679 0.04861 0.04065 -0.0845 0.9695 0.1880
-13.250 -0.7481 0.04696 0.03903 -0.0868 0.9604 0.1931
-13.000 -0.7417 0.04433 0.03625 -0.0889 0.9490 0.1993
-12.750 -0.7207 0.04261 0.03451 -0.0916 0.9419 0.2050
-12.500 -0.7056 0.04082 0.03265 -0.0935 0.9312 0.2110
-12.250 -0.6871 0.03870 0.03038 -0.0966 0.9243 0.2178
-12.000 -0.6646 0.03758 0.02927 -0.0985 0.9146 0.2236
-11.750 -0.6485 0.03574 0.02724 -0.1007 0.9061 0.2306
-11.500 -0.6251 0.03476 0.02625 -0.1024 0.8979 0.2364
-11.250 -0.6077 0.03367 0.02509 -0.1033 0.8884 0.2426
-11.000 -0.5914 0.03227 0.02348 -0.1047 0.8808 0.2493
-10.750 -0.5740 0.03179 0.02304 -0.1042 0.8706 0.2544
-10.500 -0.5590 0.03090 0.02204 -0.1042 0.8623 0.2608
-10.250 -0.5472 0.02999 0.02098 -0.1037 0.8547 0.2666
-10.000 -0.5305 0.02965 0.02068 -0.1028 0.8468 0.2714
-9.750 -0.5171 0.02906 0.02001 -0.1018 0.8396 0.2772
-9.500 -0.5088 0.02826 0.01900 -0.1003 0.8333 0.2832
-9.250 -0.4926 0.02805 0.01888 -0.0988 0.8258 0.2877
-9.000 -0.4795 0.02769 0.01849 -0.0971 0.8191 0.2930
-8.750 -0.4694 0.02718 0.01785 -0.0951 0.8136 0.2989
-8.500 -0.4549 0.02679 0.01742 -0.0935 0.8085 0.3043
-8.250 -0.4442 0.02662 0.01729 -0.0910 0.8018 0.3090
-8.000 -0.4348 0.02632 0.01695 -0.0884 0.7956 0.3146
-7.750 -0.4275 0.02593 0.01642 -0.0855 0.7904 0.3204
-7.500 -0.4025 0.02565 0.01616 -0.0852 0.7868 0.3258
-7.250 -0.3974 0.02560 0.01615 -0.0816 0.7804 0.3306
-7.000 -0.3924 0.02548 0.01598 -0.0779 0.7742 0.3362
-6.750 -0.3843 0.02527 0.01568 -0.0747 0.7691 0.3419
-6.500 -0.3582 0.02502 0.01548 -0.0745 0.7653 0.3475
-6.250 -0.3441 0.02488 0.01531 -0.0723 0.7608 0.3536
-6.000 -0.3422 0.02488 0.01528 -0.0680 0.7540 0.3593
-5.750 -0.3268 0.02472 0.01514 -0.0659 0.7486 0.3652
-5.500 -0.3052 0.02450 0.01494 -0.0649 0.7441 0.3715
-5.250 -0.2837 0.02422 0.01457 -0.0638 0.7401 0.3791
-5.000 -0.2766 0.02421 0.01458 -0.0603 0.7338 0.3852
-4.750 -0.2635 0.02416 0.01462 -0.0577 0.7274 0.3914
-4.500 -0.2464 0.02397 0.01440 -0.0558 0.7222 0.3991
-4.250 -0.2227 0.02370 0.01410 -0.0550 0.7183 0.4072
-4.000 -0.2017 0.02356 0.01400 -0.0538 0.7139 0.4150
-3.750 -0.2006 0.02367 0.01415 -0.0491 0.7064 0.4225
-3.500 -0.1842 0.02358 0.01412 -0.0471 0.7010 0.4305
-3.250 -0.1615 0.02338 0.01394 -0.0460 0.6967 0.4400
-3.000 -0.1333 0.02313 0.01369 -0.0459 0.6932 0.4504
-2.750 -0.1342 0.02337 0.01405 -0.0408 0.6855 0.4587
-2.500 -0.1225 0.02339 0.01410 -0.0378 0.6793 0.4687
-2.250 -0.0995 0.02328 0.01403 -0.0367 0.6747 0.4801
-2.000 -0.0698 0.02310 0.01385 -0.0367 0.6711 0.4922
-1.750 -0.0718 0.02336 0.01417 -0.0314 0.6633 0.5029
-1.500 -0.0597 0.02346 0.01431 -0.0285 0.6568 0.5135
-1.250 -0.0359 0.02331 0.01412 -0.0275 0.6521 0.5270
-1.000 -0.0041 0.02312 0.01387 -0.0278 0.6486 0.5403
-0.750 -0.0152 0.02351 0.01435 -0.0210 0.6392 0.5489
-0.500 0.0011 0.02347 0.01427 -0.0187 0.6332 0.5607
-0.250 0.0330 0.02326 0.01403 -0.0190 0.6291 0.5715
0.000 0.0354 0.02343 0.01420 -0.0145 0.6217 0.5816
0.250 0.0419 0.02352 0.01432 -0.0106 0.6141 0.5904
0.500 0.0721 0.02331 0.01408 -0.0106 0.6094 0.6006
0.750 0.0900 0.02324 0.01397 -0.0086 0.6037 0.6103
1.000 0.0815 0.02350 0.01432 -0.0022 0.5944 0.6171
1.250 0.1092 0.02327 0.01403 -0.0019 0.5894 0.6272
1.500 0.1317 0.02317 0.01394 -0.0006 0.5836 0.6352
1.750 0.1230 0.02351 0.01435 0.0056 0.5741 0.6423
2.000 0.1514 0.02325 0.01401 0.0058 0.5690 0.6519
2.250 0.1659 0.02336 0.01417 0.0082 0.5621 0.6586
2.500 0.1704 0.02366 0.01451 0.0121 0.5535 0.6661
2.750 0.2013 0.02334 0.01411 0.0120 0.5485 0.6753
3.000 0.2059 0.02375 0.01461 0.0157 0.5400 0.6816
3.250 0.2220 0.02387 0.01473 0.0177 0.5327 0.6893
3.750 0.2539 0.02416 0.01504 0.0215 0.5186 0.7045
4.000 0.2764 0.02415 0.01502 0.0225 0.5120 0.7126
4.250 0.3131 0.02378 0.01456 0.0215 0.5073 0.7214
4.500 0.3075 0.02460 0.01550 0.0261 0.4977 0.7284
4.750 0.3336 0.02452 0.01538 0.0266 0.4915 0.7374
5.000 0.3593 0.02451 0.01535 0.0270 0.4856 0.7460
5.250 0.3647 0.02512 0.01604 0.0299 0.4773 0.7556
5.500 0.3922 0.02504 0.01593 0.0301 0.4716 0.7677
5.750 0.4160 0.02520 0.01613 0.0306 0.4653 0.7802
6.000 0.4264 0.02578 0.01678 0.0326 0.4576 0.7929
6.250 0.4592 0.02571 0.01670 0.0319 0.4518 0.8044
6.500 0.4852 0.02596 0.01697 0.0317 0.4457 0.8158
6.750 0.4997 0.02662 0.01772 0.0327 0.4383 0.8293
7.000 0.5373 0.02664 0.01775 0.0308 0.4323 0.8414
7.500 0.5973 0.02781 0.01907 0.0277 0.4187 0.8720
7.750 0.6448 0.02799 0.01924 0.0239 0.4127 0.8865
8.000 0.6872 0.02853 0.01981 0.0203 0.4064 0.9027
8.250 0.7211 0.02956 0.02094 0.0172 0.3987 0.9196
8.500 0.7696 0.02984 0.02119 0.0131 0.3929 0.9325
8.750 0.8047 0.03059 0.02196 0.0103 0.3865 0.9488
9.000 0.8293 0.03174 0.02318 0.0086 0.3796 0.9686
9.250 0.8662 0.03220 0.02359 0.0061 0.3740 0.9860
9.500 0.8999 0.03290 0.02422 0.0041 0.3689 1.0000
9.750 0.8841 0.03419 0.02556 0.0087 0.3634 1.0000
10.000 0.8863 0.03499 0.02632 0.0113 0.3581 1.0000
10.250 0.9037 0.03523 0.02647 0.0125 0.3539 1.0000
10.500 0.9086 0.03615 0.02738 0.0146 0.3492 1.0000
10.750 0.8983 0.03790 0.02921 0.0177 0.3435 1.0000
11.000 0.9064 0.03877 0.03005 0.0194 0.3386 1.0000
11.250 0.9295 0.03884 0.03004 0.0200 0.3347 1.0000
11.500 0.9226 0.04069 0.03195 0.0224 0.3294 1.0000
11.750 0.9139 0.04277 0.03411 0.0247 0.3237 1.0000
12.000 0.9270 0.04349 0.03480 0.0257 0.3192 1.0000
12.250 0.9557 0.04323 0.03444 0.0260 0.3157 1.0000
12.500 0.9277 0.04690 0.03828 0.0287 0.3095 1.0000
12.750 0.9234 0.04904 0.04048 0.0302 0.3041 1.0000
13.000 0.9443 0.04926 0.04064 0.0307 0.3002 1.0000
13.250 0.9549 0.05033 0.04170 0.0315 0.2959 1.0000
13.500 0.9147 0.05579 0.04736 0.0334 0.2887 1.0000
13.750 0.9290 0.05659 0.04814 0.0340 0.2844 1.0000
14.000 0.9632 0.05560 0.04704 0.0342 0.2812 1.0000
14.250 0.8876 0.06525 0.05700 0.0353 0.2718 1.0000
14.500 0.9050 0.06579 0.05751 0.0357 0.2678 1.0000
14.750 0.9445 0.06398 0.05559 0.0362 0.2650 1.0000
15.000 0.8462 0.07761 0.06954 0.0354 0.2528 1.0000
15.250 0.8839 0.07567 0.06753 0.0360 0.2505 1.0000
15.500 0.9302 0.07279 0.06454 0.0367 0.2484 1.0000
15.750 0.8315 0.08772 0.07976 0.0345 0.2351 1.0000
16.000 0.8736 0.08498 0.07695 0.0354 0.2337 1.0000
16.500 0.7960 0.10139 0.09357 0.0319 0.2149 1.0000
16.750 0.8643 0.09471 0.08676 0.0339 0.2170 1.0000
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