RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 200,000 Max Cl/Cd: 73.72 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf33-il-200000-n5.txt Download as CSV file: xf-raf33-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 33 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3038 0.10290 0.09847 -0.0348 0.7104 0.0422
-10.000 -0.3052 0.09901 0.09457 -0.0370 0.7056 0.0423
-9.750 -0.3036 0.09537 0.09093 -0.0386 0.7001 0.0423
-9.500 -0.3039 0.08903 0.08454 -0.0393 0.6956 0.0352
-9.250 -0.2974 0.08640 0.08186 -0.0395 0.6908 0.0349
-9.000 -0.3025 0.08228 0.07776 -0.0417 0.6860 0.0350
-8.750 -0.3184 0.07720 0.07270 -0.0454 0.6813 0.0353
-8.500 -0.3321 0.07303 0.06849 -0.0464 0.6770 0.0353
-8.250 -0.3376 0.06993 0.06533 -0.0460 0.6733 0.0353
-8.000 -0.3377 0.06675 0.06212 -0.0460 0.6687 0.0351
-7.750 -0.3391 0.06304 0.05833 -0.0460 0.6644 0.0350
-7.500 -0.3388 0.05925 0.05441 -0.0458 0.6605 0.0349
-7.250 -0.3372 0.05528 0.05026 -0.0454 0.6571 0.0349
-7.000 -0.3467 0.04698 0.04156 -0.0445 0.6540 0.0355
-6.750 -0.3376 0.04441 0.03885 -0.0433 0.6495 0.0359
-6.500 -0.3253 0.04214 0.03643 -0.0420 0.6455 0.0361
-6.250 -0.3200 0.03762 0.03149 -0.0399 0.6425 0.0362
-6.000 -0.3084 0.03462 0.02816 -0.0380 0.6391 0.0364
-5.750 -0.2937 0.03218 0.02544 -0.0363 0.6348 0.0367
-5.500 -0.2773 0.03003 0.02300 -0.0347 0.6307 0.0370
-5.250 -0.2576 0.02869 0.02144 -0.0335 0.6270 0.0378
-5.000 -0.2380 0.02711 0.01954 -0.0321 0.6238 0.0386
-4.750 -0.2175 0.02536 0.01748 -0.0309 0.6198 0.0392
-4.500 -0.1956 0.02373 0.01551 -0.0297 0.6157 0.0396
-4.250 -0.1720 0.02241 0.01389 -0.0288 0.6119 0.0402
-4.000 -0.1473 0.02131 0.01248 -0.0280 0.6086 0.0407
-3.750 -0.1214 0.02038 0.01133 -0.0275 0.6050 0.0413
-3.500 -0.0949 0.01960 0.01036 -0.0271 0.6009 0.0419
-3.250 -0.0682 0.01889 0.00951 -0.0268 0.5969 0.0428
-3.000 -0.0417 0.01829 0.00887 -0.0266 0.5934 0.0439
-2.750 -0.0149 0.01783 0.00834 -0.0263 0.5902 0.0450
-2.500 0.0122 0.01734 0.00782 -0.0261 0.5861 0.0459
-2.250 0.0392 0.01688 0.00733 -0.0258 0.5821 0.0470
-2.000 0.0659 0.01646 0.00684 -0.0255 0.5784 0.0482
-1.750 0.0925 0.01610 0.00639 -0.0251 0.5754 0.0494
-1.500 0.1188 0.01581 0.00607 -0.0247 0.5716 0.0507
-1.250 0.1442 0.01543 0.00575 -0.0242 0.5675 0.0530
-1.000 0.1701 0.01521 0.00554 -0.0238 0.5637 0.0562
-0.750 0.1958 0.01501 0.00528 -0.0232 0.5604 0.0594
-0.500 0.2212 0.01478 0.00505 -0.0227 0.5572 0.0633
-0.250 0.2466 0.01462 0.00493 -0.0222 0.5529 0.0690
0.000 0.2720 0.01444 0.00480 -0.0216 0.5489 0.0782
0.250 0.2972 0.01428 0.00469 -0.0210 0.5454 0.0969
0.500 0.3220 0.01410 0.00457 -0.0204 0.5424 0.1272
0.750 0.3450 0.01385 0.00460 -0.0196 0.5381 0.1894
1.000 0.3661 0.01348 0.00460 -0.0183 0.5340 0.3080
1.250 0.5042 0.01269 0.00545 -0.0402 0.5283 0.9624
1.500 0.5639 0.01298 0.00564 -0.0467 0.5235 0.9796
1.750 0.6359 0.01297 0.00556 -0.0560 0.5176 0.9957
2.000 0.6762 0.01289 0.00540 -0.0587 0.5133 1.0000
2.250 0.7003 0.01295 0.00539 -0.0580 0.5094 1.0000
2.500 0.7243 0.01302 0.00548 -0.0574 0.5041 1.0000
2.750 0.7483 0.01307 0.00550 -0.0568 0.4992 1.0000
3.000 0.7722 0.01313 0.00547 -0.0560 0.4946 1.0000
3.250 0.7960 0.01321 0.00560 -0.0554 0.4885 1.0000
3.500 0.8197 0.01328 0.00564 -0.0547 0.4829 1.0000
3.750 0.8433 0.01336 0.00567 -0.0540 0.4783 1.0000
4.000 0.8669 0.01346 0.00583 -0.0533 0.4722 1.0000
4.250 0.8904 0.01356 0.00592 -0.0526 0.4671 1.0000
4.500 0.9138 0.01367 0.00601 -0.0519 0.4624 1.0000
4.750 0.9370 0.01380 0.00620 -0.0512 0.4561 1.0000
5.000 0.9600 0.01393 0.00631 -0.0504 0.4507 1.0000
5.250 0.9830 0.01407 0.00647 -0.0496 0.4451 1.0000
5.500 1.0057 0.01423 0.00668 -0.0489 0.4390 1.0000
5.750 1.0282 0.01438 0.00682 -0.0480 0.4335 1.0000
6.000 1.0505 0.01456 0.00706 -0.0472 0.4267 1.0000
6.250 1.0725 0.01475 0.00727 -0.0463 0.4202 1.0000
6.500 1.0942 0.01496 0.00751 -0.0453 0.4134 1.0000
6.750 1.1153 0.01518 0.00775 -0.0443 0.4051 1.0000
7.000 1.1360 0.01542 0.00802 -0.0433 0.3962 1.0000
7.250 1.1560 0.01568 0.00828 -0.0421 0.3871 1.0000
7.500 1.1760 0.01597 0.00863 -0.0410 0.3781 1.0000
7.750 1.1951 0.01629 0.00895 -0.0397 0.3701 1.0000
8.000 1.2139 0.01663 0.00935 -0.0384 0.3606 1.0000
8.250 1.2316 0.01700 0.00974 -0.0370 0.3515 1.0000
8.500 1.2483 0.01742 0.01017 -0.0354 0.3423 1.0000
8.750 1.2648 0.01784 0.01064 -0.0338 0.3337 1.0000
9.000 1.2790 0.01834 0.01114 -0.0319 0.3251 1.0000
9.250 1.2922 0.01886 0.01171 -0.0299 0.3142 1.0000
9.500 1.3022 0.01949 0.01234 -0.0274 0.3024 1.0000
9.750 1.3090 0.02021 0.01305 -0.0246 0.2909 1.0000
10.000 1.3119 0.02099 0.01382 -0.0212 0.2808 1.0000
10.250 1.3103 0.02176 0.01462 -0.0171 0.2718 1.0000
10.500 1.3059 0.02288 0.01575 -0.0135 0.2635 1.0000
10.750 1.3058 0.02409 0.01699 -0.0108 0.2535 1.0000
11.000 1.3050 0.02551 0.01842 -0.0085 0.2429 1.0000
11.250 1.3029 0.02718 0.02006 -0.0064 0.2317 1.0000
11.500 1.3014 0.02895 0.02183 -0.0045 0.2209 1.0000
11.750 1.2992 0.03090 0.02377 -0.0029 0.2078 1.0000
12.000 1.2977 0.03289 0.02577 -0.0015 0.1957 1.0000
12.250 1.2934 0.03521 0.02807 -0.0002 0.1807 1.0000
12.500 1.2890 0.03762 0.03048 0.0010 0.1656 1.0000
12.750 1.2799 0.04054 0.03333 0.0021 0.1443 1.0000
13.000 1.2572 0.04485 0.03741 0.0031 0.1068 1.0000
13.250 1.2402 0.04886 0.04129 0.0039 0.0905 1.0000
13.500 1.2305 0.05234 0.04474 0.0043 0.0818 1.0000
13.750 1.2231 0.05571 0.04814 0.0046 0.0756 1.0000
14.000 1.2210 0.05859 0.05110 0.0048 0.0693 1.0000
14.250 1.2151 0.06200 0.05456 0.0048 0.0632 1.0000
14.500 1.2121 0.06514 0.05777 0.0048 0.0560 1.0000
14.750 1.2074 0.06858 0.06126 0.0046 0.0494 1.0000
15.000 1.2013 0.07229 0.06500 0.0042 0.0431 1.0000
15.250 1.1926 0.07641 0.06913 0.0037 0.0367 1.0000
15.500 1.1859 0.08037 0.07314 0.0031 0.0329 1.0000
15.750 1.1788 0.08446 0.07729 0.0024 0.0301 1.0000
16.000 1.1717 0.08861 0.08150 0.0016 0.0277 1.0000
16.250 1.1638 0.09296 0.08591 0.0007 0.0264 1.0000
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