AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 200,000 Max Cl/Cd: 59.93 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5048-il-200000.txt Download as CSV file: xf-as5048-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AS5048 (18%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.3498 0.12618 0.12287 -0.0444 1.0000 0.0684
-13.500 -0.3476 0.12353 0.12025 -0.0448 1.0000 0.0705
-13.250 -0.5328 0.11494 0.11137 -0.0481 1.0000 0.0667
-13.000 -0.5145 0.11540 0.11184 -0.0453 1.0000 0.0680
-12.750 -0.5113 0.11211 0.10857 -0.0459 1.0000 0.0697
-12.500 -0.5295 0.10340 0.09990 -0.0510 1.0000 0.0721
-12.250 -0.5784 0.09078 0.08724 -0.0592 1.0000 0.0724
-12.000 -0.6185 0.08294 0.07932 -0.0629 1.0000 0.0722
-11.750 -0.6533 0.07716 0.07344 -0.0643 1.0000 0.0722
-11.500 -0.6849 0.07263 0.06882 -0.0642 1.0000 0.0726
-11.250 -0.7154 0.06908 0.06516 -0.0628 1.0000 0.0731
-11.000 -0.7467 0.06654 0.06253 -0.0596 1.0000 0.0737
-10.750 -0.7838 0.06520 0.06094 -0.0559 0.9928 0.0753
-9.750 -0.7268 0.03589 0.02868 -0.0588 0.9167 0.0320
-9.500 -0.6816 0.03271 0.02517 -0.0628 0.9095 0.0314
-9.250 -0.6355 0.03037 0.02254 -0.0667 0.9013 0.0318
-9.000 -0.5942 0.02883 0.02065 -0.0700 0.8918 0.0331
-8.750 -0.5412 0.02680 0.01854 -0.0740 0.8858 0.0340
-8.500 -0.4969 0.02551 0.01729 -0.0763 0.8793 0.0352
-8.250 -0.4642 0.02459 0.01635 -0.0773 0.8725 0.0366
-8.000 -0.4399 0.02379 0.01551 -0.0771 0.8658 0.0382
-7.750 -0.4191 0.02292 0.01457 -0.0767 0.8599 0.0404
-7.500 -0.4030 0.02192 0.01359 -0.0760 0.8548 0.0428
-7.250 -0.3884 0.02105 0.01269 -0.0749 0.8494 0.0451
-7.000 -0.3754 0.02023 0.01179 -0.0734 0.8442 0.0473
-6.750 -0.3680 0.01940 0.01092 -0.0711 0.8398 0.0508
-6.500 -0.3549 0.01875 0.01022 -0.0694 0.8362 0.0567
-6.250 -0.3433 0.01797 0.00948 -0.0674 0.8325 0.0680
-6.000 -0.3507 0.01606 0.00835 -0.0631 0.8285 0.1938
-5.750 -0.3676 0.01366 0.00742 -0.0571 0.8244 0.4549
-5.500 -0.3465 0.01441 0.00865 -0.0548 0.8215 0.5894
-5.250 -0.3209 0.01532 0.00949 -0.0536 0.8188 0.6201
-5.000 -0.2927 0.01639 0.01054 -0.0527 0.8162 0.6374
-4.750 -0.2643 0.01751 0.01163 -0.0517 0.8134 0.6527
-4.500 -0.2293 0.01928 0.01348 -0.0504 0.8106 0.6630
-4.250 -0.2009 0.02003 0.01417 -0.0495 0.8080 0.6737
-4.000 -0.1695 0.02073 0.01482 -0.0491 0.8058 0.6793
-3.750 -0.1470 0.02060 0.01455 -0.0489 0.8032 0.6886
-3.500 -0.1194 0.02093 0.01489 -0.0482 0.8004 0.6916
-3.250 -0.0934 0.02111 0.01503 -0.0477 0.7976 0.6962
-3.000 -0.0731 0.02076 0.01457 -0.0475 0.7944 0.7050
-2.750 -0.0451 0.02094 0.01473 -0.0471 0.7915 0.7075
-2.500 -0.0175 0.02107 0.01482 -0.0468 0.7889 0.7109
-2.250 0.0083 0.02106 0.01472 -0.0469 0.7864 0.7163
-2.000 0.0284 0.02077 0.01440 -0.0465 0.7830 0.7222
-1.750 0.0532 0.02085 0.01449 -0.0458 0.7796 0.7247
-1.500 0.0786 0.02088 0.01450 -0.0454 0.7762 0.7279
-1.250 0.1043 0.02082 0.01438 -0.0455 0.7730 0.7322
-1.000 0.1306 0.02061 0.01405 -0.0463 0.7699 0.7379
-0.750 0.1532 0.02063 0.01412 -0.0454 0.7661 0.7401
-0.500 0.1762 0.02067 0.01418 -0.0446 0.7616 0.7427
-0.250 0.2022 0.02063 0.01413 -0.0444 0.7574 0.7456
0.000 0.2305 0.02055 0.01399 -0.0449 0.7536 0.7490
0.250 0.2546 0.02049 0.01389 -0.0450 0.7488 0.7528
0.500 0.2784 0.02036 0.01377 -0.0448 0.7432 0.7555
0.750 0.3056 0.02027 0.01367 -0.0447 0.7387 0.7576
1.000 0.3354 0.02025 0.01361 -0.0451 0.7351 0.7596
1.250 0.3555 0.02028 0.01371 -0.0441 0.7288 0.7619
1.500 0.3826 0.02020 0.01363 -0.0442 0.7235 0.7646
1.750 0.4133 0.02007 0.01345 -0.0450 0.7193 0.7673
2.000 0.4379 0.02006 0.01346 -0.0450 0.7132 0.7698
2.250 0.4655 0.01992 0.01332 -0.0454 0.7069 0.7719
2.500 0.4961 0.01967 0.01305 -0.0457 0.7020 0.7738
2.750 0.5187 0.01956 0.01301 -0.0448 0.6938 0.7760
3.000 0.5490 0.01920 0.01264 -0.0451 0.6866 0.7780
3.250 0.5771 0.01898 0.01242 -0.0452 0.6797 0.7800
3.500 0.6036 0.01875 0.01223 -0.0451 0.6718 0.7821
3.750 0.6374 0.01842 0.01185 -0.0462 0.6667 0.7846
4.000 0.6602 0.01830 0.01183 -0.0456 0.6575 0.7872
4.250 0.6921 0.01793 0.01143 -0.0464 0.6512 0.7891
4.500 0.7157 0.01768 0.01128 -0.0456 0.6421 0.7909
4.750 0.7450 0.01726 0.01089 -0.0457 0.6345 0.7927
5.000 0.7686 0.01702 0.01075 -0.0449 0.6242 0.7949
5.250 0.7977 0.01660 0.01034 -0.0450 0.6154 0.7975
5.500 0.8216 0.01630 0.01011 -0.0442 0.6022 0.8002
5.750 0.8464 0.01602 0.00989 -0.0437 0.5872 0.8026
6.000 0.8721 0.01575 0.00963 -0.0433 0.5698 0.8049
6.250 0.8945 0.01555 0.00943 -0.0423 0.5471 0.8070
6.500 0.9153 0.01544 0.00923 -0.0408 0.5201 0.8091
6.750 0.9331 0.01557 0.00923 -0.0389 0.4880 0.8119
7.000 0.9488 0.01589 0.00940 -0.0368 0.4549 0.8150
7.250 0.9630 0.01634 0.00969 -0.0346 0.4224 0.8180
7.500 0.9762 0.01687 0.01009 -0.0323 0.3914 0.8209
7.750 0.9879 0.01744 0.01054 -0.0299 0.3630 0.8237
8.000 0.9950 0.01801 0.01100 -0.0265 0.3390 0.8266
8.250 1.0030 0.01859 0.01154 -0.0234 0.3164 0.8299
8.500 1.0131 0.01929 0.01218 -0.0210 0.2954 0.8337
8.750 1.0241 0.02007 0.01288 -0.0189 0.2768 0.8379
9.000 1.0347 0.02083 0.01361 -0.0168 0.2606 0.8420
9.250 1.0450 0.02159 0.01438 -0.0147 0.2466 0.8465
9.500 1.0559 0.02242 0.01521 -0.0129 0.2340 0.8513
9.750 1.0667 0.02337 0.01610 -0.0113 0.2227 0.8566
10.000 1.0770 0.02416 0.01698 -0.0095 0.2118 0.8622
10.250 1.0875 0.02507 0.01794 -0.0079 0.2018 0.8692
10.500 1.0959 0.02613 0.01897 -0.0061 0.1926 0.8773
10.750 1.1048 0.02699 0.01999 -0.0043 0.1834 0.8888
11.250 1.1051 0.02854 0.02175 0.0027 0.1689 1.0000
11.500 1.1186 0.02993 0.02305 0.0027 0.1600 1.0000
11.750 1.1325 0.03125 0.02444 0.0025 0.1509 1.0000
12.000 1.1443 0.03268 0.02585 0.0028 0.1428 1.0000
12.250 1.1550 0.03414 0.02733 0.0030 0.1348 1.0000
12.500 1.1653 0.03565 0.02885 0.0035 0.1274 1.0000
12.750 1.1740 0.03722 0.03042 0.0039 0.1205 1.0000
13.000 1.1829 0.03881 0.03204 0.0045 0.1141 1.0000
13.250 1.1906 0.04047 0.03374 0.0050 0.1081 1.0000
13.500 1.1979 0.04218 0.03542 0.0057 0.1028 1.0000
13.750 1.2053 0.04391 0.03724 0.0062 0.0977 1.0000
14.000 1.2113 0.04571 0.03898 0.0068 0.0932 1.0000
14.250 1.2182 0.04755 0.04093 0.0074 0.0890 1.0000
14.500 1.2240 0.04947 0.04292 0.0078 0.0851 1.0000
14.750 1.2303 0.05131 0.04469 0.0084 0.0815 1.0000
15.000 1.2359 0.05335 0.04686 0.0089 0.0784 1.0000
15.250 1.2404 0.05551 0.04913 0.0091 0.0752 1.0000
15.500 1.2450 0.05765 0.05130 0.0093 0.0725 1.0000
15.750 1.2541 0.05933 0.05291 0.0101 0.0695 1.0000
16.000 1.2545 0.06205 0.05584 0.0101 0.0675 1.0000
16.250 1.2564 0.06463 0.05856 0.0100 0.0652 1.0000
16.500 1.2597 0.06707 0.06104 0.0099 0.0631 1.0000
16.750 1.2675 0.06894 0.06287 0.0103 0.0609 1.0000
17.000 1.2686 0.07172 0.06580 0.0104 0.0592 1.0000
17.250 1.2643 0.07526 0.06955 0.0098 0.0577 1.0000
17.500 1.2618 0.07864 0.07308 0.0091 0.0561 1.0000
17.750 1.2613 0.08179 0.07632 0.0084 0.0546 1.0000
18.000 1.2647 0.08437 0.07891 0.0080 0.0531 1.0000
18.250 1.2714 0.08641 0.08093 0.0085 0.0514 1.0000
18.500 1.2601 0.09123 0.08600 0.0069 0.0507 1.0000
18.750 1.2484 0.09628 0.09128 0.0050 0.0499 1.0000
19.000 1.2366 0.10148 0.09670 0.0028 0.0491 1.0000
19.250 1.2241 0.10695 0.10237 0.0004 0.0482 1.0000
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Polar data table (+)
Polar graphs
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