RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF-48 AIRFOIL (raf48-il) Reynolds number: 100,000 Max Cl/Cd: 49.19 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf48-il-100000-n5.txt Download as CSV file: xf-raf48-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6096 0.06797 0.06229 -0.0699 1.0000 0.0501
-12.250 -0.6625 0.05813 0.05223 -0.0768 1.0000 0.0495
-12.000 -0.6977 0.05282 0.04670 -0.0781 1.0000 0.0495
-11.750 -0.7255 0.04930 0.04297 -0.0765 1.0000 0.0498
-11.500 -0.7508 0.04676 0.04024 -0.0726 1.0000 0.0502
-11.250 -0.7727 0.04466 0.03793 -0.0676 1.0000 0.0506
-11.000 -0.7922 0.04257 0.03555 -0.0626 1.0000 0.0512
-10.750 -0.7936 0.04140 0.03441 -0.0592 1.0000 0.0519
-10.500 -0.7987 0.04053 0.03354 -0.0550 0.9998 0.0526
-10.250 -0.7734 0.03870 0.03157 -0.0568 0.9883 0.0542
-10.000 -0.7502 0.03673 0.02932 -0.0581 0.9766 0.0561
-9.750 -0.7274 0.03459 0.02677 -0.0591 0.9656 0.0584
-9.500 -0.6991 0.03279 0.02475 -0.0607 0.9574 0.0603
-9.250 -0.6707 0.03155 0.02345 -0.0618 0.9480 0.0622
-9.000 -0.6395 0.03024 0.02196 -0.0634 0.9411 0.0648
-8.750 -0.6123 0.02890 0.02031 -0.0640 0.9314 0.0676
-8.500 -0.5807 0.02766 0.01900 -0.0655 0.9245 0.0701
-8.250 -0.5532 0.02673 0.01802 -0.0660 0.9151 0.0726
-8.000 -0.5225 0.02577 0.01687 -0.0669 0.9082 0.0765
-7.750 -0.4971 0.02492 0.01592 -0.0669 0.8985 0.0800
-7.500 -0.4692 0.02418 0.01514 -0.0672 0.8911 0.0838
-7.250 -0.4449 0.02351 0.01432 -0.0667 0.8817 0.0884
-7.000 -0.4191 0.02285 0.01364 -0.0666 0.8743 0.0936
-6.750 -0.3958 0.02233 0.01304 -0.0659 0.8652 0.1001
-6.500 -0.3706 0.02175 0.01243 -0.0656 0.8582 0.1070
-6.250 -0.3480 0.02133 0.01190 -0.0647 0.8494 0.1158
-6.000 -0.3227 0.02082 0.01141 -0.0643 0.8432 0.1253
-5.750 -0.3020 0.02045 0.01103 -0.0631 0.8342 0.1356
-5.500 -0.2767 0.02006 0.01057 -0.0626 0.8275 0.1481
-5.250 -0.2550 0.01974 0.01023 -0.0614 0.8188 0.1610
-5.000 -0.2309 0.01935 0.00984 -0.0606 0.8108 0.1744
-4.750 -0.2093 0.01905 0.00954 -0.0594 0.8015 0.1885
-4.500 -0.1851 0.01871 0.00919 -0.0586 0.7938 0.2045
-4.250 -0.1629 0.01843 0.00895 -0.0575 0.7855 0.2224
-4.000 -0.1393 0.01815 0.00868 -0.0566 0.7783 0.2435
-3.750 -0.1156 0.01785 0.00843 -0.0557 0.7720 0.2669
-3.500 -0.0939 0.01759 0.00825 -0.0545 0.7642 0.2924
-3.250 -0.0696 0.01726 0.00797 -0.0537 0.7582 0.3216
-3.000 -0.0482 0.01700 0.00784 -0.0524 0.7508 0.3553
-2.750 -0.0262 0.01669 0.00769 -0.0512 0.7439 0.3984
-2.500 -0.0026 0.01636 0.00752 -0.0501 0.7382 0.4530
-2.250 0.0175 0.01613 0.00752 -0.0485 0.7302 0.5118
-2.000 0.0418 0.01583 0.00746 -0.0474 0.7239 0.5799
-1.750 0.0670 0.01567 0.00752 -0.0463 0.7170 0.6513
-1.500 0.0949 0.01561 0.00760 -0.0457 0.7097 0.7118
-1.250 0.1278 0.01556 0.00758 -0.0460 0.7041 0.7626
-1.000 0.1579 0.01565 0.00772 -0.0459 0.6955 0.8026
-0.750 0.1930 0.01569 0.00771 -0.0467 0.6887 0.8364
-0.500 0.2286 0.01580 0.00779 -0.0478 0.6810 0.8659
-0.250 0.2726 0.01592 0.00785 -0.0505 0.6733 0.8889
0.000 0.3164 0.01603 0.00788 -0.0532 0.6660 0.9067
0.250 0.3589 0.01616 0.00794 -0.0559 0.6569 0.9206
0.500 0.3999 0.01625 0.00794 -0.0582 0.6495 0.9333
0.750 0.4428 0.01642 0.00807 -0.0610 0.6401 0.9485
1.000 0.4882 0.01651 0.00807 -0.0644 0.6324 0.9638
1.250 0.5286 0.01659 0.00811 -0.0670 0.6224 0.9760
1.500 0.5664 0.01661 0.00806 -0.0692 0.6140 0.9850
1.750 0.6044 0.01664 0.00806 -0.0716 0.6047 0.9933
2.000 0.6419 0.01663 0.00801 -0.0738 0.5958 1.0000
2.250 0.6599 0.01668 0.00802 -0.0722 0.5873 1.0000
2.500 0.6779 0.01677 0.00808 -0.0706 0.5791 1.0000
2.750 0.6961 0.01686 0.00814 -0.0689 0.5708 1.0000
3.000 0.7144 0.01698 0.00823 -0.0673 0.5628 1.0000
3.250 0.7328 0.01712 0.00834 -0.0656 0.5545 1.0000
3.500 0.7517 0.01727 0.00846 -0.0640 0.5468 1.0000
3.750 0.7704 0.01743 0.00860 -0.0624 0.5383 1.0000
4.000 0.7896 0.01760 0.00875 -0.0608 0.5301 1.0000
4.250 0.8087 0.01778 0.00890 -0.0592 0.5211 1.0000
4.500 0.8276 0.01799 0.00909 -0.0576 0.5123 1.0000
4.750 0.8475 0.01817 0.00924 -0.0561 0.5038 1.0000
5.000 0.8662 0.01842 0.00950 -0.0545 0.4948 1.0000
5.250 0.8865 0.01862 0.00966 -0.0531 0.4866 1.0000
5.500 0.9049 0.01892 0.00998 -0.0514 0.4777 1.0000
5.750 0.9254 0.01914 0.01016 -0.0500 0.4695 1.0000
6.000 0.9431 0.01947 0.01054 -0.0483 0.4605 1.0000
6.250 0.9637 0.01972 0.01074 -0.0469 0.4525 1.0000
6.500 0.9805 0.02008 0.01118 -0.0451 0.4431 1.0000
6.750 1.0011 0.02035 0.01140 -0.0437 0.4350 1.0000
7.000 1.0164 0.02074 0.01188 -0.0417 0.4253 1.0000
7.250 1.0359 0.02106 0.01217 -0.0402 0.4170 1.0000
7.500 1.0507 0.02147 0.01268 -0.0381 0.4072 1.0000
7.750 1.0680 0.02183 0.01305 -0.0363 0.3984 1.0000
8.000 1.0822 0.02225 0.01354 -0.0341 0.3885 1.0000
8.250 1.0966 0.02268 0.01403 -0.0319 0.3788 1.0000
8.500 1.1105 0.02309 0.01446 -0.0297 0.3689 1.0000
8.750 1.1212 0.02359 0.01506 -0.0270 0.3582 1.0000
9.000 1.1330 0.02407 0.01557 -0.0245 0.3482 1.0000
9.250 1.1405 0.02458 0.01613 -0.0213 0.3375 1.0000
9.500 1.1461 0.02516 0.01679 -0.0180 0.3265 1.0000
9.750 1.1520 0.02579 0.01743 -0.0149 0.3153 1.0000
10.000 1.1569 0.02650 0.01813 -0.0119 0.3034 1.0000
10.250 1.1603 0.02739 0.01904 -0.0090 0.2903 1.0000
10.500 1.1628 0.02841 0.02006 -0.0062 0.2766 1.0000
10.750 1.1640 0.02960 0.02123 -0.0037 0.2623 1.0000
11.000 1.1646 0.03097 0.02256 -0.0014 0.2482 1.0000
11.250 1.1654 0.03245 0.02401 0.0007 0.2352 1.0000
11.500 1.1670 0.03402 0.02555 0.0025 0.2241 1.0000
11.750 1.1694 0.03564 0.02719 0.0040 0.2140 1.0000
12.000 1.1725 0.03730 0.02890 0.0053 0.2050 1.0000
12.250 1.1739 0.03912 0.03072 0.0066 0.1964 1.0000
12.500 1.1769 0.04096 0.03266 0.0077 0.1880 1.0000
12.750 1.1772 0.04301 0.03470 0.0087 0.1801 1.0000
13.000 1.1783 0.04514 0.03694 0.0095 0.1715 1.0000
13.250 1.1776 0.04744 0.03926 0.0102 0.1639 1.0000
13.500 1.1768 0.04988 0.04179 0.0107 0.1558 1.0000
13.750 1.1748 0.05251 0.04447 0.0111 0.1481 1.0000
14.000 1.1719 0.05534 0.04738 0.0113 0.1402 1.0000
14.250 1.1687 0.05834 0.05045 0.0114 0.1323 1.0000
14.500 1.1628 0.06171 0.05384 0.0112 0.1246 1.0000
14.750 1.1584 0.06511 0.05734 0.0109 0.1163 1.0000
15.000 1.1518 0.06881 0.06105 0.0104 0.1094 1.0000
15.250 1.1467 0.07250 0.06483 0.0098 0.1021 1.0000
15.500 1.1400 0.07644 0.06879 0.0090 0.0958 1.0000
15.750 1.1336 0.08045 0.07287 0.0081 0.0896 1.0000
16.000 1.1272 0.08451 0.07695 0.0071 0.0846 1.0000
16.250 1.1217 0.08855 0.08106 0.0061 0.0798 1.0000
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