NACA 2415 (naca2415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2415 (naca2415-il) Reynolds number: 200,000 Max Cl/Cd: 61.55 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2415-il-200000-n5.txt Download as CSV file: xf-naca2415-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2415
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9068 0.08451 0.07935 -0.0527 1.0000 0.0383
-16.000 -0.9335 0.07638 0.07103 -0.0579 1.0000 0.0384
-15.750 -0.9519 0.06989 0.06437 -0.0620 1.0000 0.0387
-15.500 -0.9661 0.06429 0.05860 -0.0655 1.0000 0.0389
-15.250 -0.9772 0.05935 0.05350 -0.0684 1.0000 0.0392
-15.000 -0.9859 0.05498 0.04897 -0.0708 1.0000 0.0395
-14.750 -0.9924 0.05110 0.04493 -0.0728 1.0000 0.0399
-14.500 -0.9968 0.04768 0.04136 -0.0742 1.0000 0.0403
-14.250 -0.9998 0.04465 0.03816 -0.0751 1.0000 0.0407
-14.000 -1.0014 0.04198 0.03532 -0.0754 1.0000 0.0412
-13.750 -1.0020 0.03965 0.03279 -0.0753 1.0000 0.0417
-13.500 -0.9997 0.03773 0.03078 -0.0746 1.0000 0.0422
-13.250 -0.9955 0.03616 0.02916 -0.0735 1.0000 0.0427
-13.000 -0.9916 0.03476 0.02772 -0.0721 1.0000 0.0432
-12.750 -0.9884 0.03350 0.02641 -0.0701 1.0000 0.0437
-12.500 -0.9867 0.03240 0.02524 -0.0674 1.0000 0.0442
-12.250 -0.9870 0.03145 0.02422 -0.0639 1.0000 0.0447
-12.000 -0.9862 0.03056 0.02326 -0.0603 1.0000 0.0452
-11.750 -0.9817 0.02966 0.02227 -0.0572 1.0000 0.0459
-11.500 -0.9761 0.02883 0.02134 -0.0542 1.0000 0.0466
-11.250 -0.9691 0.02804 0.02044 -0.0512 1.0000 0.0474
-11.000 -0.9625 0.02723 0.01962 -0.0482 1.0000 0.0481
-10.750 -0.9545 0.02651 0.01889 -0.0453 1.0000 0.0489
-10.500 -0.9451 0.02584 0.01818 -0.0426 1.0000 0.0498
-10.250 -0.9347 0.02519 0.01748 -0.0401 1.0000 0.0508
-10.000 -0.9185 0.02450 0.01671 -0.0386 0.9992 0.0520
-9.750 -0.8886 0.02371 0.01580 -0.0397 0.9960 0.0536
-9.500 -0.8584 0.02287 0.01497 -0.0410 0.9931 0.0552
-9.250 -0.8296 0.02218 0.01425 -0.0419 0.9890 0.0572
-9.000 -0.7986 0.02155 0.01352 -0.0431 0.9853 0.0598
-8.750 -0.7666 0.02085 0.01282 -0.0446 0.9823 0.0624
-8.500 -0.7377 0.02026 0.01220 -0.0453 0.9775 0.0653
-8.250 -0.7064 0.01970 0.01158 -0.0464 0.9733 0.0688
-8.000 -0.6729 0.01911 0.01100 -0.0480 0.9701 0.0730
-7.750 -0.6430 0.01862 0.01048 -0.0487 0.9651 0.0779
-7.500 -0.6117 0.01812 0.00998 -0.0497 0.9602 0.0836
-7.250 -0.5770 0.01762 0.00949 -0.0514 0.9568 0.0901
-7.000 -0.5458 0.01722 0.00904 -0.0522 0.9517 0.0971
-6.750 -0.5167 0.01677 0.00863 -0.0527 0.9453 0.1046
-6.500 -0.4833 0.01634 0.00821 -0.0540 0.9411 0.1132
-6.250 -0.4551 0.01601 0.00786 -0.0541 0.9341 0.1220
-6.000 -0.4255 0.01561 0.00751 -0.0545 0.9276 0.1319
-5.750 -0.3926 0.01522 0.00714 -0.0556 0.9231 0.1430
-5.500 -0.3675 0.01492 0.00686 -0.0550 0.9136 0.1539
-5.250 -0.3364 0.01457 0.00653 -0.0557 0.9075 0.1673
-5.000 -0.3097 0.01427 0.00628 -0.0554 0.8985 0.1811
-4.750 -0.2800 0.01394 0.00599 -0.0557 0.8911 0.1966
-4.500 -0.2528 0.01366 0.00576 -0.0556 0.8818 0.2128
-4.250 -0.2234 0.01338 0.00551 -0.0557 0.8734 0.2305
-4.000 -0.1963 0.01314 0.00530 -0.0555 0.8633 0.2480
-3.750 -0.1671 0.01288 0.00507 -0.0556 0.8544 0.2662
-3.500 -0.1404 0.01267 0.00489 -0.0552 0.8430 0.2838
-3.250 -0.1123 0.01245 0.00469 -0.0551 0.8326 0.3024
-2.750 -0.0582 0.01206 0.00437 -0.0545 0.8090 0.3415
-2.500 -0.0309 0.01187 0.00421 -0.0542 0.7973 0.3634
-2.250 -0.0043 0.01169 0.00408 -0.0538 0.7845 0.3880
-2.000 0.0220 0.01153 0.00398 -0.0533 0.7715 0.4152
-1.750 0.0482 0.01136 0.00388 -0.0528 0.7586 0.4471
-1.500 0.0743 0.01120 0.00381 -0.0523 0.7457 0.4829
-1.250 0.1000 0.01106 0.00378 -0.0516 0.7320 0.5213
-1.000 0.1258 0.01095 0.00375 -0.0510 0.7188 0.5592
-0.750 0.1518 0.01086 0.00372 -0.0503 0.7057 0.5948
-0.500 0.1776 0.01079 0.00372 -0.0497 0.6923 0.6294
-0.250 0.2033 0.01072 0.00373 -0.0489 0.6792 0.6634
0.000 0.2290 0.01068 0.00375 -0.0482 0.6662 0.6966
0.250 0.2547 0.01066 0.00379 -0.0474 0.6530 0.7284
0.500 0.2804 0.01066 0.00385 -0.0466 0.6397 0.7589
0.750 0.3064 0.01069 0.00392 -0.0458 0.6274 0.7899
1.000 0.3328 0.01076 0.00401 -0.0451 0.6151 0.8188
1.250 0.3595 0.01085 0.00409 -0.0445 0.6022 0.8463
1.500 0.3876 0.01095 0.00419 -0.0441 0.5888 0.8703
1.750 0.4169 0.01109 0.00429 -0.0441 0.5747 0.8921
2.000 0.4474 0.01124 0.00438 -0.0444 0.5587 0.9114
2.250 0.4796 0.01142 0.00449 -0.0450 0.5434 0.9285
2.500 0.5135 0.01159 0.00461 -0.0461 0.5300 0.9440
2.750 0.5493 0.01177 0.00475 -0.0477 0.5172 0.9587
3.000 0.5870 0.01196 0.00489 -0.0497 0.5044 0.9724
3.500 0.6672 0.01235 0.00518 -0.0549 0.4786 0.9915
3.750 0.7061 0.01253 0.00532 -0.0573 0.4653 0.9979
4.000 0.7325 0.01271 0.00544 -0.0572 0.4530 1.0000
4.250 0.7520 0.01289 0.00556 -0.0557 0.4389 1.0000
4.500 0.7717 0.01308 0.00569 -0.0541 0.4237 1.0000
4.750 0.7916 0.01327 0.00585 -0.0526 0.4097 1.0000
5.000 0.8117 0.01349 0.00602 -0.0512 0.3972 1.0000
5.250 0.8314 0.01373 0.00620 -0.0496 0.3846 1.0000
5.500 0.8515 0.01396 0.00641 -0.0481 0.3712 1.0000
5.750 0.8716 0.01421 0.00663 -0.0467 0.3577 1.0000
6.000 0.8914 0.01449 0.00687 -0.0452 0.3436 1.0000
6.250 0.9109 0.01480 0.00712 -0.0437 0.3285 1.0000
6.500 0.9302 0.01514 0.00740 -0.0421 0.3116 1.0000
6.750 0.9492 0.01550 0.00770 -0.0406 0.2929 1.0000
7.000 0.9677 0.01591 0.00803 -0.0390 0.2724 1.0000
7.250 0.9852 0.01637 0.00839 -0.0373 0.2518 1.0000
7.500 1.0023 0.01688 0.00879 -0.0356 0.2328 1.0000
7.750 1.0193 0.01740 0.00924 -0.0339 0.2161 1.0000
8.000 1.0361 0.01795 0.00972 -0.0321 0.2012 1.0000
8.250 1.0530 0.01848 0.01021 -0.0305 0.1870 1.0000
8.500 1.0696 0.01902 0.01073 -0.0288 0.1732 1.0000
8.750 1.0845 0.01958 0.01125 -0.0268 0.1601 1.0000
9.000 1.0983 0.02019 0.01182 -0.0247 0.1478 1.0000
9.250 1.1115 0.02086 0.01246 -0.0226 0.1365 1.0000
9.500 1.1243 0.02160 0.01316 -0.0206 0.1262 1.0000
9.750 1.1366 0.02239 0.01392 -0.0186 0.1169 1.0000
10.000 1.1497 0.02317 0.01471 -0.0168 0.1089 1.0000
10.250 1.1612 0.02407 0.01561 -0.0149 0.1020 1.0000
10.500 1.1733 0.02496 0.01653 -0.0132 0.0954 1.0000
10.750 1.1842 0.02597 0.01755 -0.0115 0.0899 1.0000
11.000 1.1949 0.02701 0.01862 -0.0099 0.0846 1.0000
11.250 1.2044 0.02818 0.01982 -0.0083 0.0801 1.0000
11.500 1.2142 0.02938 0.02106 -0.0069 0.0758 1.0000
11.750 1.2211 0.03082 0.02251 -0.0054 0.0725 1.0000
12.000 1.2305 0.03215 0.02392 -0.0042 0.0694 1.0000
12.250 1.2377 0.03368 0.02551 -0.0031 0.0667 1.0000
12.500 1.2424 0.03549 0.02734 -0.0019 0.0646 1.0000
12.750 1.2490 0.03721 0.02915 -0.0010 0.0627 1.0000
13.000 1.2550 0.03902 0.03105 -0.0002 0.0608 1.0000
13.250 1.2595 0.04104 0.03314 0.0005 0.0591 1.0000
13.500 1.2620 0.04330 0.03544 0.0010 0.0577 1.0000
13.750 1.2639 0.04570 0.03789 0.0015 0.0564 1.0000
14.000 1.2681 0.04792 0.04022 0.0018 0.0551 1.0000
14.250 1.2712 0.05031 0.04271 0.0020 0.0539 1.0000
14.500 1.2733 0.05285 0.04534 0.0021 0.0528 1.0000
14.750 1.2746 0.05555 0.04811 0.0021 0.0519 1.0000
15.000 1.2750 0.05841 0.05104 0.0019 0.0511 1.0000
15.250 1.2743 0.06142 0.05408 0.0017 0.0503 1.0000
15.500 1.2757 0.06425 0.05701 0.0014 0.0495 1.0000
15.750 1.2773 0.06714 0.06002 0.0010 0.0486 1.0000
16.000 1.2782 0.07015 0.06314 0.0006 0.0477 1.0000
16.250 1.2785 0.07328 0.06636 0.0000 0.0469 1.0000
16.500 1.2785 0.07647 0.06964 -0.0007 0.0462 1.0000
16.750 1.2783 0.07972 0.07296 -0.0014 0.0456 1.0000
17.000 1.2778 0.08306 0.07636 -0.0023 0.0450 1.0000
17.250 1.2776 0.08631 0.07965 -0.0030 0.0444 1.0000
17.500 1.2773 0.08961 0.08303 -0.0039 0.0438 1.0000
17.750 1.2754 0.09333 0.08690 -0.0051 0.0431 1.0000
18.000 1.2732 0.09711 0.09082 -0.0063 0.0425 1.0000
18.250 1.2709 0.10097 0.09479 -0.0077 0.0419 1.0000
18.500 1.2681 0.10492 0.09886 -0.0092 0.0413 1.0000
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