ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.9 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad13-il-1000000.txt Download as CSV file: xf-arad13-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 13% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0089 0.08305 0.08040 -0.0206 1.0000 0.0150
-15.000 -1.1308 0.05621 0.05322 -0.0407 1.0000 0.0146
-14.750 -1.1697 0.04112 0.03770 -0.0561 1.0000 0.0144
-14.500 -1.1865 0.03754 0.03394 -0.0546 1.0000 0.0145
-14.250 -1.1938 0.03415 0.03033 -0.0533 1.0000 0.0146
-14.000 -1.1896 0.03153 0.02755 -0.0523 1.0000 0.0147
-13.750 -1.1778 0.02958 0.02546 -0.0514 1.0000 0.0149
-13.500 -1.1614 0.02805 0.02383 -0.0508 1.0000 0.0150
-13.250 -1.1423 0.02678 0.02246 -0.0502 1.0000 0.0152
-13.000 -1.1214 0.02566 0.02127 -0.0498 1.0000 0.0154
-12.750 -1.0993 0.02465 0.02017 -0.0494 1.0000 0.0155
-12.500 -1.0763 0.02369 0.01914 -0.0490 1.0000 0.0157
-12.250 -1.0526 0.02280 0.01816 -0.0487 1.0000 0.0159
-12.000 -1.0282 0.02195 0.01724 -0.0484 1.0000 0.0161
-11.750 -1.0033 0.02115 0.01636 -0.0482 1.0000 0.0164
-11.500 -0.9778 0.02040 0.01553 -0.0480 1.0000 0.0166
-11.250 -0.9518 0.01969 0.01474 -0.0478 1.0000 0.0168
-11.000 -0.9252 0.01907 0.01405 -0.0477 1.0000 0.0170
-10.750 -0.8992 0.01824 0.01313 -0.0475 1.0000 0.0173
-10.500 -0.8732 0.01737 0.01222 -0.0474 1.0000 0.0178
-10.250 -0.8459 0.01678 0.01159 -0.0474 1.0000 0.0181
-10.000 -0.8181 0.01627 0.01105 -0.0474 1.0000 0.0186
-9.750 -0.7900 0.01579 0.01053 -0.0474 1.0000 0.0190
-9.500 -0.7618 0.01533 0.01003 -0.0474 1.0000 0.0195
-9.250 -0.7333 0.01492 0.00957 -0.0474 1.0000 0.0199
-9.000 -0.7053 0.01431 0.00892 -0.0474 1.0000 0.0206
-8.750 -0.6768 0.01385 0.00846 -0.0475 1.0000 0.0213
-8.500 -0.6480 0.01349 0.00808 -0.0476 1.0000 0.0221
-8.250 -0.6185 0.01317 0.00774 -0.0478 0.9982 0.0230
-8.000 -0.5839 0.01272 0.00728 -0.0492 0.9832 0.0243
-7.750 -0.5522 0.01247 0.00701 -0.0497 0.9640 0.0256
-7.500 -0.5252 0.01228 0.00674 -0.0491 0.9407 0.0268
-7.000 -0.4720 0.01188 0.00622 -0.0478 0.8985 0.0300
-6.750 -0.4442 0.01163 0.00592 -0.0475 0.8796 0.0319
-6.500 -0.4159 0.01149 0.00571 -0.0473 0.8614 0.0338
-6.000 -0.3582 0.01115 0.00525 -0.0471 0.8277 0.0380
-5.750 -0.3290 0.01096 0.00501 -0.0471 0.8120 0.0403
-5.500 -0.2997 0.01084 0.00484 -0.0471 0.7968 0.0427
-5.250 -0.2703 0.01067 0.00462 -0.0472 0.7817 0.0453
-5.000 -0.2409 0.01056 0.00446 -0.0472 0.7663 0.0479
-4.750 -0.2113 0.01040 0.00426 -0.0473 0.7506 0.0506
-4.500 -0.1816 0.01030 0.00410 -0.0474 0.7339 0.0536
-4.250 -0.1520 0.01017 0.00393 -0.0475 0.7170 0.0570
-4.000 -0.1222 0.01010 0.00381 -0.0477 0.7014 0.0607
-3.750 -0.0925 0.00998 0.00367 -0.0478 0.6867 0.0657
-3.500 -0.0626 0.00989 0.00354 -0.0480 0.6719 0.0706
-3.250 -0.0327 0.00982 0.00344 -0.0482 0.6578 0.0757
-3.000 -0.0027 0.00971 0.00333 -0.0484 0.6441 0.0826
-2.750 0.0272 0.00964 0.00323 -0.0486 0.6302 0.0897
-2.500 0.0571 0.00959 0.00315 -0.0488 0.6157 0.0970
-2.250 0.0871 0.00953 0.00309 -0.0490 0.6015 0.1046
-2.000 0.1171 0.00948 0.00302 -0.0492 0.5872 0.1136
-1.750 0.1471 0.00945 0.00297 -0.0494 0.5732 0.1222
-1.500 0.1771 0.00944 0.00293 -0.0497 0.5593 0.1307
-1.250 0.2071 0.00939 0.00289 -0.0499 0.5461 0.1416
-1.000 0.2371 0.00938 0.00285 -0.0502 0.5319 0.1517
-0.750 0.2670 0.00939 0.00283 -0.0504 0.5174 0.1627
-0.500 0.2970 0.00937 0.00282 -0.0507 0.5032 0.1774
-0.250 0.3270 0.00935 0.00281 -0.0510 0.4890 0.1949
0.000 0.3569 0.00933 0.00281 -0.0513 0.4735 0.2194
0.250 0.3867 0.00927 0.00281 -0.0516 0.4578 0.2597
0.500 0.4165 0.00904 0.00283 -0.0521 0.4425 0.3617
0.750 0.4455 0.00843 0.00288 -0.0527 0.4264 0.6093
1.250 0.4916 0.00767 0.00298 -0.0498 0.3924 0.9531
1.500 0.5251 0.00763 0.00286 -0.0508 0.3734 1.0000
1.750 0.5547 0.00781 0.00293 -0.0511 0.3546 1.0000
2.000 0.5842 0.00801 0.00301 -0.0513 0.3351 1.0000
2.250 0.6137 0.00822 0.00310 -0.0516 0.3170 1.0000
2.500 0.6432 0.00842 0.00320 -0.0519 0.3014 1.0000
2.750 0.6726 0.00863 0.00331 -0.0521 0.2868 1.0000
3.250 0.7314 0.00903 0.00354 -0.0527 0.2618 1.0000
3.500 0.7607 0.00923 0.00367 -0.0529 0.2517 1.0000
3.750 0.7900 0.00943 0.00380 -0.0532 0.2416 1.0000
4.000 0.8193 0.00961 0.00394 -0.0534 0.2330 1.0000
4.250 0.8484 0.00984 0.00408 -0.0537 0.2241 1.0000
4.500 0.8776 0.01001 0.00422 -0.0539 0.2174 1.0000
4.750 0.9065 0.01023 0.00438 -0.0542 0.2097 1.0000
5.000 0.9356 0.01042 0.00454 -0.0544 0.2037 1.0000
5.250 0.9645 0.01061 0.00469 -0.0546 0.1978 1.0000
5.500 0.9930 0.01087 0.00489 -0.0548 0.1909 1.0000
5.750 1.0220 0.01103 0.00504 -0.0550 0.1871 1.0000
6.000 1.0506 0.01124 0.00522 -0.0552 0.1824 1.0000
6.250 1.0788 0.01152 0.00545 -0.0554 0.1766 1.0000
6.500 1.1075 0.01168 0.00562 -0.0556 0.1736 1.0000
6.750 1.1359 0.01189 0.00581 -0.0557 0.1696 1.0000
7.000 1.1638 0.01215 0.00603 -0.0559 0.1653 1.0000
7.250 1.1916 0.01241 0.00628 -0.0560 0.1614 1.0000
7.500 1.2199 0.01260 0.00647 -0.0561 0.1586 1.0000
7.750 1.2477 0.01283 0.00669 -0.0562 0.1551 1.0000
8.000 1.2749 0.01313 0.00696 -0.0563 0.1512 1.0000
8.250 1.3021 0.01341 0.00724 -0.0563 0.1479 1.0000
8.500 1.3298 0.01361 0.00746 -0.0564 0.1454 1.0000
8.750 1.3569 0.01386 0.00771 -0.0564 0.1423 1.0000
9.000 1.3834 0.01418 0.00800 -0.0564 0.1387 1.0000
9.250 1.4095 0.01453 0.00834 -0.0563 0.1354 1.0000
9.500 1.4365 0.01475 0.00859 -0.0563 0.1333 1.0000
9.750 1.4628 0.01502 0.00887 -0.0562 0.1304 1.0000
10.000 1.4884 0.01537 0.00920 -0.0561 0.1273 1.0000
10.250 1.5128 0.01580 0.00962 -0.0558 0.1237 1.0000
10.500 1.5389 0.01604 0.00990 -0.0556 0.1219 1.0000
10.750 1.5641 0.01635 0.01023 -0.0554 0.1194 1.0000
11.000 1.5883 0.01672 0.01060 -0.0551 0.1167 1.0000
11.250 1.6109 0.01722 0.01108 -0.0545 0.1134 1.0000
11.500 1.6348 0.01756 0.01146 -0.0541 0.1115 1.0000
11.750 1.6585 0.01790 0.01183 -0.0537 0.1094 1.0000
12.000 1.6808 0.01832 0.01226 -0.0531 0.1071 1.0000
12.250 1.7015 0.01883 0.01277 -0.0522 0.1045 1.0000
12.500 1.7206 0.01941 0.01337 -0.0512 0.1019 1.0000
12.750 1.7420 0.01979 0.01380 -0.0504 0.1004 1.0000
13.000 1.7615 0.02026 0.01431 -0.0494 0.0986 1.0000
13.250 1.7789 0.02083 0.01490 -0.0481 0.0966 1.0000
13.500 1.7931 0.02153 0.01562 -0.0464 0.0944 1.0000
13.750 1.8004 0.02240 0.01652 -0.0435 0.0924 1.0000
14.000 1.8130 0.02307 0.01726 -0.0415 0.0913 1.0000
14.250 1.8248 0.02386 0.01811 -0.0397 0.0899 1.0000
14.500 1.8356 0.02482 0.01911 -0.0380 0.0883 1.0000
14.750 1.8447 0.02596 0.02029 -0.0363 0.0867 1.0000
15.000 1.8513 0.02739 0.02177 -0.0347 0.0850 1.0000
15.250 1.8576 0.02896 0.02340 -0.0333 0.0834 1.0000
15.500 1.8690 0.03019 0.02470 -0.0325 0.0824 1.0000
15.750 1.8784 0.03164 0.02623 -0.0317 0.0812 1.0000
16.000 1.8857 0.03335 0.02800 -0.0309 0.0799 1.0000
16.250 1.8909 0.03532 0.03003 -0.0303 0.0786 1.0000
16.500 1.8928 0.03771 0.03246 -0.0297 0.0771 1.0000
16.750 1.8890 0.04076 0.03558 -0.0293 0.0754 1.0000
17.000 1.8964 0.04269 0.03761 -0.0291 0.0745 1.0000
17.250 1.9004 0.04503 0.04003 -0.0290 0.0734 1.0000
17.500 1.9008 0.04779 0.04287 -0.0290 0.0722 1.0000
17.750 1.8980 0.05097 0.04613 -0.0291 0.0711 1.0000
18.000 1.8914 0.05467 0.04990 -0.0294 0.0700 1.0000
18.250 1.8808 0.05898 0.05430 -0.0300 0.0689 1.0000
18.500 1.8666 0.06386 0.05927 -0.0308 0.0678 1.0000
18.750 1.8632 0.06745 0.06297 -0.0315 0.0672 1.0000
19.000 1.8569 0.07148 0.06711 -0.0324 0.0663 1.0000
19.250 1.8472 0.07601 0.07174 -0.0335 0.0654 1.0000
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