RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 30 AIRFOIL (raf30-il) Reynolds number: 200,000 Max Cl/Cd: 45.59 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf30-il-200000-n5.txt Download as CSV file: xf-raf30-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8546 0.12012 0.11587 -0.0110 1.0000 0.0222
-16.500 -0.8966 0.10636 0.10189 -0.0194 1.0000 0.0221
-16.250 -0.9268 0.09614 0.09150 -0.0257 1.0000 0.0220
-16.000 -0.9515 0.08758 0.08274 -0.0309 1.0000 0.0219
-15.750 -0.9730 0.08015 0.07509 -0.0354 1.0000 0.0221
-15.500 -0.9925 0.07357 0.06828 -0.0391 1.0000 0.0222
-15.250 -1.0091 0.06791 0.06239 -0.0419 1.0000 0.0223
-15.000 -1.0195 0.06345 0.05779 -0.0438 1.0000 0.0226
-14.750 -1.0239 0.05998 0.05423 -0.0449 1.0000 0.0229
-14.500 -1.0273 0.05679 0.05094 -0.0458 1.0000 0.0233
-14.250 -1.0306 0.05369 0.04773 -0.0465 1.0000 0.0236
-14.000 -1.0327 0.05091 0.04485 -0.0469 1.0000 0.0240
-13.750 -1.0347 0.04819 0.04198 -0.0470 1.0000 0.0244
-13.500 -1.0358 0.04574 0.03940 -0.0469 1.0000 0.0250
-13.250 -1.0362 0.04348 0.03697 -0.0464 1.0000 0.0257
-13.000 -1.0358 0.04132 0.03464 -0.0457 1.0000 0.0263
-12.750 -1.0337 0.03941 0.03253 -0.0447 1.0000 0.0270
-12.500 -1.0307 0.03768 0.03059 -0.0434 1.0000 0.0276
-12.250 -1.0253 0.03590 0.02869 -0.0420 1.0000 0.0283
-12.000 -1.0179 0.03434 0.02709 -0.0406 1.0000 0.0290
-11.750 -1.0102 0.03306 0.02576 -0.0391 1.0000 0.0297
-11.500 -1.0021 0.03186 0.02449 -0.0373 1.0000 0.0305
-11.250 -0.9935 0.03076 0.02330 -0.0355 1.0000 0.0315
-11.000 -0.9840 0.02968 0.02212 -0.0335 1.0000 0.0323
-10.750 -0.9741 0.02869 0.02101 -0.0313 1.0000 0.0332
-10.500 -0.9637 0.02779 0.01997 -0.0291 1.0000 0.0341
-10.250 -0.9542 0.02674 0.01885 -0.0267 1.0000 0.0349
-10.000 -0.9464 0.02569 0.01779 -0.0239 1.0000 0.0359
-9.750 -0.9361 0.02482 0.01690 -0.0215 1.0000 0.0369
-9.500 -0.9240 0.02402 0.01605 -0.0193 1.0000 0.0379
-9.250 -0.9113 0.02324 0.01522 -0.0170 1.0000 0.0390
-9.000 -0.8977 0.02254 0.01445 -0.0148 1.0000 0.0402
-8.750 -0.8836 0.02187 0.01369 -0.0127 1.0000 0.0414
-8.500 -0.8691 0.02122 0.01297 -0.0106 1.0000 0.0424
-8.250 -0.8576 0.02038 0.01212 -0.0080 1.0000 0.0437
-8.000 -0.8438 0.01970 0.01142 -0.0058 1.0000 0.0451
-7.750 -0.8289 0.01911 0.01080 -0.0036 1.0000 0.0469
-7.500 -0.8132 0.01858 0.01021 -0.0016 1.0000 0.0489
-7.250 -0.7972 0.01808 0.00965 0.0004 1.0000 0.0509
-7.000 -0.7824 0.01752 0.00909 0.0026 1.0000 0.0536
-6.750 -0.7670 0.01701 0.00859 0.0048 1.0000 0.0574
-6.500 -0.7516 0.01656 0.00814 0.0069 1.0000 0.0629
-6.250 -0.7370 0.01608 0.00772 0.0092 1.0000 0.0736
-6.000 -0.7053 0.01546 0.00723 0.0078 0.9949 0.0986
-5.750 -0.6730 0.01488 0.00676 0.0063 0.9882 0.1234
-5.500 -0.6406 0.01434 0.00632 0.0049 0.9814 0.1493
-5.250 -0.6088 0.01380 0.00591 0.0036 0.9737 0.1798
-5.000 -0.5792 0.01326 0.00556 0.0028 0.9647 0.2198
-4.750 -0.5481 0.01275 0.00523 0.0017 0.9566 0.2658
-4.500 -0.5168 0.01230 0.00494 0.0007 0.9478 0.3076
-4.250 -0.4859 0.01187 0.00468 -0.0002 0.9383 0.3477
-4.000 -0.4524 0.01147 0.00443 -0.0015 0.9303 0.3903
-3.750 -0.4220 0.01113 0.00424 -0.0021 0.9194 0.4299
-3.500 -0.3894 0.01085 0.00407 -0.0031 0.9097 0.4675
-3.250 -0.3567 0.01063 0.00393 -0.0041 0.8993 0.5008
-3.000 -0.3259 0.01047 0.00380 -0.0046 0.8873 0.5252
-2.750 -0.2954 0.01033 0.00369 -0.0050 0.8754 0.5493
-2.500 -0.2664 0.01020 0.00362 -0.0050 0.8632 0.5791
-2.250 -0.2385 0.01011 0.00356 -0.0047 0.8506 0.6050
-2.000 -0.2113 0.01004 0.00349 -0.0044 0.8375 0.6220
-1.750 -0.1842 0.00999 0.00343 -0.0040 0.8245 0.6362
-1.500 -0.1572 0.00995 0.00337 -0.0036 0.8114 0.6495
-1.250 -0.1306 0.00991 0.00331 -0.0030 0.7968 0.6627
-1.000 -0.1044 0.00989 0.00325 -0.0024 0.7809 0.6757
-0.500 -0.0522 0.00986 0.00318 -0.0012 0.7523 0.7013
-0.250 -0.0261 0.00985 0.00317 -0.0006 0.7393 0.7137
0.000 0.0000 0.00985 0.00316 0.0000 0.7263 0.7262
0.250 0.0261 0.00985 0.00317 0.0006 0.7137 0.7392
0.500 0.0522 0.00986 0.00318 0.0012 0.7013 0.7524
0.750 0.0785 0.00988 0.00320 0.0018 0.6889 0.7659
1.000 0.1045 0.00989 0.00325 0.0024 0.6758 0.7810
1.250 0.1306 0.00991 0.00331 0.0030 0.6628 0.7968
1.500 0.1572 0.00995 0.00337 0.0036 0.6495 0.8114
1.750 0.1842 0.00999 0.00343 0.0040 0.6360 0.8244
2.000 0.2113 0.01004 0.00349 0.0044 0.6220 0.8374
2.250 0.2385 0.01011 0.00356 0.0047 0.6052 0.8507
2.500 0.2664 0.01020 0.00362 0.0050 0.5793 0.8632
2.750 0.2953 0.01033 0.00369 0.0050 0.5489 0.8753
3.000 0.3259 0.01047 0.00380 0.0046 0.5252 0.8874
3.250 0.3567 0.01063 0.00393 0.0041 0.5005 0.8994
3.500 0.3893 0.01086 0.00407 0.0032 0.4662 0.9097
3.750 0.4220 0.01113 0.00424 0.0021 0.4298 0.9194
4.000 0.4523 0.01147 0.00443 0.0016 0.3894 0.9303
4.250 0.4858 0.01188 0.00468 0.0002 0.3472 0.9382
4.500 0.5168 0.01230 0.00494 -0.0007 0.3073 0.9477
4.750 0.5481 0.01275 0.00523 -0.0017 0.2660 0.9566
5.000 0.5792 0.01327 0.00556 -0.0028 0.2192 0.9647
5.250 0.6088 0.01381 0.00592 -0.0036 0.1788 0.9737
5.500 0.6406 0.01434 0.00632 -0.0049 0.1489 0.9814
5.750 0.6731 0.01488 0.00676 -0.0063 0.1234 0.9882
6.000 0.7053 0.01547 0.00723 -0.0078 0.0976 0.9949
6.500 0.7516 0.01655 0.00814 -0.0069 0.0629 1.0000
6.750 0.7670 0.01702 0.00860 -0.0048 0.0573 1.0000
7.000 0.7824 0.01751 0.00909 -0.0027 0.0537 1.0000
7.250 0.7972 0.01808 0.00965 -0.0004 0.0509 1.0000
7.500 0.8133 0.01858 0.01020 0.0016 0.0489 1.0000
7.750 0.8289 0.01911 0.01080 0.0036 0.0468 1.0000
8.000 0.8439 0.01969 0.01142 0.0057 0.0451 1.0000
8.250 0.8577 0.02037 0.01211 0.0080 0.0437 1.0000
8.500 0.8694 0.02121 0.01296 0.0105 0.0424 1.0000
8.750 0.8837 0.02187 0.01369 0.0127 0.0414 1.0000
9.000 0.8978 0.02253 0.01444 0.0148 0.0402 1.0000
9.250 0.9114 0.02324 0.01522 0.0170 0.0390 1.0000
9.500 0.9241 0.02401 0.01604 0.0192 0.0380 1.0000
9.750 0.9362 0.02482 0.01690 0.0215 0.0369 1.0000
10.000 0.9465 0.02568 0.01779 0.0239 0.0359 1.0000
10.250 0.9543 0.02675 0.01886 0.0266 0.0349 1.0000
10.500 0.9637 0.02777 0.01996 0.0291 0.0340 1.0000
10.750 0.9743 0.02868 0.02100 0.0313 0.0333 1.0000
11.000 0.9844 0.02970 0.02213 0.0334 0.0324 1.0000
11.250 0.9936 0.03075 0.02329 0.0354 0.0314 1.0000
11.500 1.0025 0.03188 0.02451 0.0373 0.0305 1.0000
11.750 1.0104 0.03305 0.02575 0.0390 0.0296 1.0000
12.000 1.0180 0.03431 0.02705 0.0406 0.0289 1.0000
12.250 1.0255 0.03590 0.02868 0.0420 0.0282 1.0000
12.500 1.0307 0.03763 0.03055 0.0433 0.0276 1.0000
12.750 1.0341 0.03937 0.03250 0.0446 0.0270 1.0000
13.000 1.0356 0.04131 0.03464 0.0456 0.0262 1.0000
13.250 1.0365 0.04344 0.03694 0.0464 0.0255 1.0000
13.500 1.0364 0.04573 0.03938 0.0468 0.0250 1.0000
13.750 1.0357 0.04813 0.04193 0.0469 0.0244 1.0000
14.000 1.0337 0.05085 0.04478 0.0468 0.0240 1.0000
14.250 1.0314 0.05367 0.04772 0.0464 0.0236 1.0000
14.500 1.0291 0.05662 0.05075 0.0457 0.0232 1.0000
14.750 1.0242 0.06007 0.05433 0.0448 0.0230 1.0000
15.000 1.0201 0.06349 0.05782 0.0437 0.0226 1.0000
15.250 1.0108 0.06781 0.06228 0.0419 0.0224 1.0000
15.500 0.9950 0.07334 0.06803 0.0392 0.0223 1.0000
15.750 0.9747 0.08005 0.07498 0.0353 0.0221 1.0000
16.000 0.9528 0.08751 0.08266 0.0309 0.0220 1.0000
16.250 0.9279 0.09615 0.09149 0.0255 0.0220 1.0000
16.500 0.8967 0.10664 0.10218 0.0190 0.0221 1.0000
16.750 0.8556 0.12023 0.11597 0.0107 0.0222 1.0000
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