RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF-48 AIRFOIL (raf48-il) Reynolds number: 200,000 Max Cl/Cd: 67.76 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf48-il-200000-n5.txt Download as CSV file: xf-raf48-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF-48 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7708 0.06747 0.06280 -0.0688 1.0000 0.0306
-14.500 -0.8027 0.05880 0.05391 -0.0751 1.0000 0.0305
-14.250 -0.8228 0.05279 0.04769 -0.0792 1.0000 0.0308
-14.000 -0.8386 0.04810 0.04280 -0.0817 1.0000 0.0311
-13.750 -0.8513 0.04436 0.03887 -0.0829 1.0000 0.0315
-13.500 -0.8613 0.04134 0.03565 -0.0829 1.0000 0.0319
-13.250 -0.8705 0.03880 0.03288 -0.0820 1.0000 0.0324
-13.000 -0.8757 0.03684 0.03077 -0.0804 1.0000 0.0330
-12.750 -0.8745 0.03551 0.02942 -0.0784 1.0000 0.0335
-12.500 -0.8737 0.03434 0.02821 -0.0760 1.0000 0.0339
-12.250 -0.8735 0.03339 0.02722 -0.0730 1.0000 0.0346
-12.000 -0.8752 0.03246 0.02622 -0.0693 1.0000 0.0352
-11.750 -0.8775 0.03159 0.02525 -0.0653 1.0000 0.0358
-11.500 -0.8774 0.03067 0.02423 -0.0615 1.0000 0.0365
-11.250 -0.8572 0.02931 0.02264 -0.0617 0.9873 0.0377
-11.000 -0.8308 0.02802 0.02126 -0.0629 0.9744 0.0388
-10.750 -0.8013 0.02702 0.02022 -0.0645 0.9622 0.0401
-10.500 -0.7707 0.02601 0.01907 -0.0661 0.9502 0.0415
-10.250 -0.7389 0.02495 0.01783 -0.0678 0.9392 0.0431
-10.000 -0.7071 0.02390 0.01661 -0.0694 0.9282 0.0446
-9.750 -0.6769 0.02297 0.01564 -0.0707 0.9165 0.0461
-9.500 -0.6472 0.02221 0.01478 -0.0717 0.9048 0.0477
-9.250 -0.6192 0.02149 0.01392 -0.0722 0.8933 0.0496
-9.000 -0.5948 0.02087 0.01313 -0.0719 0.8812 0.0511
-8.750 -0.5732 0.02015 0.01238 -0.0711 0.8699 0.0527
-8.500 -0.5506 0.01960 0.01176 -0.0704 0.8596 0.0545
-8.250 -0.5296 0.01913 0.01120 -0.0693 0.8487 0.0566
-8.000 -0.5074 0.01867 0.01060 -0.0683 0.8396 0.0588
-7.750 -0.4870 0.01813 0.01004 -0.0671 0.8304 0.0610
-7.500 -0.4655 0.01769 0.00954 -0.0660 0.8222 0.0635
-7.250 -0.4435 0.01730 0.00907 -0.0649 0.8137 0.0666
-7.000 -0.4214 0.01689 0.00860 -0.0639 0.8066 0.0703
-6.750 -0.3991 0.01653 0.00822 -0.0629 0.7989 0.0749
-6.500 -0.3760 0.01619 0.00780 -0.0620 0.7924 0.0800
-6.250 -0.3534 0.01586 0.00746 -0.0610 0.7847 0.0865
-6.000 -0.3303 0.01555 0.00712 -0.0600 0.7769 0.0941
-5.750 -0.3069 0.01530 0.00681 -0.0591 0.7679 0.1032
-5.500 -0.2835 0.01503 0.00651 -0.0582 0.7593 0.1131
-5.250 -0.2600 0.01478 0.00625 -0.0573 0.7516 0.1232
-5.000 -0.2358 0.01457 0.00600 -0.0566 0.7449 0.1336
-4.750 -0.2111 0.01437 0.00576 -0.0559 0.7394 0.1452
-4.500 -0.1873 0.01414 0.00557 -0.0551 0.7330 0.1567
-4.250 -0.1630 0.01394 0.00536 -0.0543 0.7269 0.1692
-4.000 -0.1383 0.01375 0.00515 -0.0537 0.7217 0.1830
-3.750 -0.1142 0.01356 0.00500 -0.0529 0.7155 0.1984
-3.500 -0.0901 0.01336 0.00485 -0.0521 0.7093 0.2166
-3.250 -0.0657 0.01317 0.00468 -0.0514 0.7041 0.2397
-3.000 -0.0421 0.01296 0.00457 -0.0506 0.6978 0.2660
-2.750 -0.0184 0.01276 0.00445 -0.0497 0.6918 0.2937
-2.500 0.0057 0.01256 0.00430 -0.0489 0.6866 0.3221
-2.250 0.0286 0.01235 0.00421 -0.0479 0.6799 0.3545
-2.000 0.0511 0.01211 0.00412 -0.0468 0.6735 0.3973
-1.750 0.0734 0.01187 0.00403 -0.0456 0.6680 0.4510
-1.500 0.0949 0.01163 0.00400 -0.0442 0.6612 0.5046
-1.250 0.1165 0.01141 0.00396 -0.0428 0.6550 0.5603
-1.000 0.1381 0.01119 0.00396 -0.0412 0.6489 0.6239
-0.750 0.1610 0.01104 0.00401 -0.0399 0.6414 0.6822
-0.500 0.1862 0.01095 0.00401 -0.0390 0.6350 0.7304
-0.250 0.2125 0.01090 0.00408 -0.0383 0.6270 0.7715
0.000 0.2411 0.01089 0.00410 -0.0381 0.6199 0.8060
0.250 0.2714 0.01090 0.00414 -0.0383 0.6124 0.8355
0.500 0.3042 0.01093 0.00417 -0.0391 0.6040 0.8637
0.750 0.3460 0.01100 0.00424 -0.0417 0.5951 0.8862
1.000 0.3874 0.01109 0.00429 -0.0444 0.5861 0.9016
1.250 0.4275 0.01120 0.00437 -0.0468 0.5768 0.9142
1.500 0.4732 0.01134 0.00443 -0.0503 0.5674 0.9245
1.750 0.5149 0.01149 0.00457 -0.0530 0.5567 0.9366
2.000 0.5512 0.01167 0.00468 -0.0546 0.5473 0.9483
2.250 0.5837 0.01182 0.00479 -0.0556 0.5375 0.9588
2.500 0.6191 0.01196 0.00488 -0.0572 0.5276 0.9654
2.750 0.6510 0.01211 0.00496 -0.0581 0.5185 0.9733
3.000 0.6857 0.01225 0.00508 -0.0597 0.5083 0.9806
3.250 0.7232 0.01240 0.00517 -0.0618 0.4981 0.9876
3.500 0.7604 0.01257 0.00527 -0.0640 0.4869 0.9942
3.750 0.7972 0.01270 0.00536 -0.0661 0.4762 0.9992
4.000 0.8188 0.01285 0.00545 -0.0651 0.4677 1.0000
4.250 0.8372 0.01298 0.00558 -0.0634 0.4591 1.0000
4.500 0.8553 0.01318 0.00571 -0.0617 0.4516 1.0000
4.750 0.8745 0.01334 0.00589 -0.0602 0.4437 1.0000
5.000 0.8933 0.01355 0.00606 -0.0585 0.4363 1.0000
5.250 0.9127 0.01375 0.00626 -0.0570 0.4288 1.0000
5.500 0.9317 0.01397 0.00647 -0.0554 0.4209 1.0000
5.750 0.9511 0.01420 0.00670 -0.0539 0.4136 1.0000
6.000 0.9705 0.01442 0.00694 -0.0524 0.4062 1.0000
6.250 0.9895 0.01468 0.00719 -0.0508 0.3991 1.0000
6.500 1.0087 0.01491 0.00746 -0.0492 0.3912 1.0000
6.750 1.0269 0.01519 0.00772 -0.0475 0.3835 1.0000
7.000 1.0456 0.01543 0.00801 -0.0459 0.3749 1.0000
7.250 1.0630 0.01573 0.00831 -0.0440 0.3671 1.0000
7.500 1.0810 0.01598 0.00863 -0.0423 0.3582 1.0000
7.750 1.0973 0.01630 0.00895 -0.0403 0.3494 1.0000
8.000 1.1130 0.01660 0.00929 -0.0382 0.3387 1.0000
8.250 1.1269 0.01695 0.00965 -0.0358 0.3259 1.0000
8.500 1.1383 0.01736 0.01004 -0.0331 0.3110 1.0000
8.750 1.1462 0.01782 0.01046 -0.0297 0.2952 1.0000
9.000 1.1506 0.01832 0.01091 -0.0258 0.2798 1.0000
9.250 1.1543 0.01893 0.01147 -0.0220 0.2638 1.0000
9.500 1.1593 0.01963 0.01211 -0.0187 0.2493 1.0000
9.750 1.1642 0.02042 0.01286 -0.0157 0.2356 1.0000
10.000 1.1688 0.02134 0.01373 -0.0128 0.2220 1.0000
10.250 1.1737 0.02234 0.01469 -0.0103 0.2104 1.0000
10.500 1.1812 0.02331 0.01567 -0.0082 0.1996 1.0000
10.750 1.1888 0.02433 0.01671 -0.0063 0.1908 1.0000
11.000 1.1951 0.02550 0.01788 -0.0044 0.1821 1.0000
11.250 1.2036 0.02660 0.01901 -0.0029 0.1739 1.0000
11.750 1.2170 0.02921 0.02166 0.0000 0.1577 1.0000
12.000 1.2218 0.03072 0.02319 0.0014 0.1503 1.0000
12.250 1.2285 0.03217 0.02468 0.0025 0.1419 1.0000
12.500 1.2330 0.03382 0.02637 0.0036 0.1343 1.0000
12.750 1.2366 0.03561 0.02817 0.0046 0.1257 1.0000
13.000 1.2402 0.03745 0.03005 0.0055 0.1168 1.0000
13.250 1.2413 0.03957 0.03218 0.0064 0.1082 1.0000
13.500 1.2412 0.04185 0.03447 0.0071 0.0988 1.0000
13.750 1.2409 0.04424 0.03687 0.0077 0.0884 1.0000
14.000 1.2395 0.04684 0.03948 0.0082 0.0795 1.0000
14.250 1.2366 0.04967 0.04230 0.0085 0.0719 1.0000
14.500 1.2325 0.05273 0.04538 0.0087 0.0663 1.0000
14.750 1.2300 0.05572 0.04841 0.0087 0.0616 1.0000
15.000 1.2252 0.05907 0.05179 0.0086 0.0582 1.0000
15.250 1.2234 0.06215 0.05496 0.0083 0.0553 1.0000
15.500 1.2200 0.06551 0.05839 0.0080 0.0530 1.0000
15.750 1.2145 0.06921 0.06214 0.0074 0.0507 1.0000
16.000 1.2103 0.07280 0.06582 0.0068 0.0490 1.0000
16.250 1.2080 0.07622 0.06934 0.0062 0.0472 1.0000
16.500 1.2039 0.07995 0.07315 0.0054 0.0455 1.0000
16.750 1.1984 0.08389 0.07716 0.0044 0.0442 1.0000
17.000 1.1915 0.08810 0.08142 0.0033 0.0430 1.0000
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