NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.56 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722343-il-1000000.txt Download as CSV file: xf-nl722343-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-43 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5077 0.08994 0.08825 -0.0244 1.0000 0.0099
-9.250 -0.5091 0.08577 0.08409 -0.0264 1.0000 0.0101
-9.000 -0.5138 0.08088 0.07923 -0.0290 1.0000 0.0102
-7.250 -0.5048 0.02519 0.02291 -0.0489 0.9904 0.0111
-7.000 -0.4845 0.02205 0.01963 -0.0508 0.9881 0.0113
-6.750 -0.4615 0.01889 0.01630 -0.0526 0.9864 0.0115
-6.500 -0.4367 0.01579 0.01300 -0.0544 0.9851 0.0119
-6.250 -0.4171 0.01307 0.01004 -0.0544 0.9804 0.0126
-6.000 -0.3958 0.00826 0.00450 -0.0544 0.9774 0.0144
-5.750 -0.3673 0.00698 0.00316 -0.0556 0.9760 0.0148
-5.500 -0.3377 0.00609 0.00218 -0.0568 0.9747 0.0159
-5.250 -0.3389 0.01357 0.00859 -0.0537 0.9747 0.0114
-5.000 -0.3067 0.01237 0.00727 -0.0547 0.9739 0.0114
-4.750 -0.2787 0.01175 0.00662 -0.0549 0.9707 0.0118
-4.500 -0.2510 0.01088 0.00569 -0.0549 0.9673 0.0119
-4.250 -0.2211 0.01015 0.00492 -0.0554 0.9648 0.0121
-4.000 -0.1899 0.00955 0.00429 -0.0562 0.9622 0.0126
-3.750 -0.1587 0.00906 0.00376 -0.0569 0.9590 0.0132
-3.500 -0.1321 0.00870 0.00337 -0.0566 0.9524 0.0137
-3.250 -0.1026 0.00822 0.00284 -0.0569 0.9481 0.0144
-3.000 -0.0747 0.00786 0.00246 -0.0569 0.9417 0.0154
-2.750 -0.0459 0.00762 0.00217 -0.0569 0.9304 0.0168
-2.500 -0.0200 0.00738 0.00186 -0.0562 0.9143 0.0193
-2.250 0.0059 0.00718 0.00162 -0.0555 0.8992 0.0254
-2.000 0.0304 0.00668 0.00140 -0.0549 0.8889 0.1126
-1.750 0.0527 0.00576 0.00119 -0.0544 0.8813 0.3382
-1.500 0.0731 0.00477 0.00114 -0.0533 0.8734 0.6499
-1.250 0.1009 0.00487 0.00119 -0.0531 0.8655 0.6729
-1.000 0.1280 0.00497 0.00129 -0.0526 0.8569 0.6909
-0.750 0.1547 0.00510 0.00144 -0.0521 0.8474 0.7075
-0.500 0.1813 0.00524 0.00157 -0.0515 0.8366 0.7216
-0.250 0.2081 0.00534 0.00164 -0.0509 0.8233 0.7293
0.000 0.2351 0.00544 0.00166 -0.0506 0.8073 0.7328
0.250 0.2617 0.00543 0.00159 -0.0502 0.7871 0.7353
0.500 0.2877 0.00550 0.00155 -0.0496 0.7566 0.7363
0.750 0.3084 0.00586 0.00152 -0.0480 0.6570 0.7367
1.000 0.3285 0.00640 0.00162 -0.0464 0.5465 0.7369
1.250 0.3509 0.00686 0.00171 -0.0454 0.4546 0.7372
1.500 0.3746 0.00725 0.00180 -0.0447 0.3794 0.7376
1.750 0.3991 0.00759 0.00188 -0.0442 0.3175 0.7380
2.000 0.4241 0.00790 0.00198 -0.0437 0.2655 0.7383
2.250 0.4496 0.00817 0.00207 -0.0433 0.2263 0.7385
2.500 0.4756 0.00839 0.00217 -0.0430 0.2002 0.7388
2.750 0.5019 0.00858 0.00227 -0.0428 0.1828 0.7391
3.000 0.5287 0.00872 0.00238 -0.0426 0.1731 0.7393
3.250 0.5555 0.00886 0.00249 -0.0424 0.1662 0.7396
3.500 0.5824 0.00898 0.00259 -0.0422 0.1611 0.7400
3.750 0.6090 0.00915 0.00273 -0.0420 0.1551 0.7403
4.000 0.6358 0.00927 0.00287 -0.0418 0.1518 0.7407
4.250 0.6628 0.00937 0.00299 -0.0416 0.1484 0.7411
4.500 0.6895 0.00951 0.00311 -0.0414 0.1436 0.7415
4.750 0.7158 0.00969 0.00328 -0.0412 0.1379 0.7419
5.000 0.7428 0.00977 0.00339 -0.0411 0.1337 0.7424
5.250 0.7692 0.00994 0.00353 -0.0409 0.1278 0.7429
5.500 0.7957 0.01008 0.00370 -0.0406 0.1229 0.7435
5.750 0.8223 0.01021 0.00383 -0.0404 0.1166 0.7442
6.000 0.8486 0.01038 0.00399 -0.0402 0.1087 0.7448
6.250 0.8743 0.01059 0.00416 -0.0399 0.0938 0.7453
6.500 0.8986 0.01099 0.00442 -0.0394 0.0729 0.7458
6.750 0.9223 0.01146 0.00480 -0.0388 0.0551 0.7464
7.000 0.9452 0.01204 0.00526 -0.0381 0.0347 0.7469
7.250 0.9681 0.01265 0.00579 -0.0373 0.0232 0.7475
7.500 0.9922 0.01308 0.00624 -0.0367 0.0202 0.7483
7.750 1.0159 0.01356 0.00678 -0.0360 0.0180 0.7493
8.000 1.0400 0.01394 0.00723 -0.0355 0.0167 0.7503
8.250 1.0634 0.01444 0.00776 -0.0348 0.0154 0.7513
8.500 1.0851 0.01514 0.00856 -0.0339 0.0142 0.7523
8.750 1.1086 0.01557 0.00906 -0.0332 0.0137 0.7534
9.000 1.1314 0.01609 0.00965 -0.0324 0.0131 0.7546
9.250 1.1537 0.01663 0.01026 -0.0316 0.0126 0.7559
9.500 1.1753 0.01723 0.01093 -0.0308 0.0121 0.7573
9.750 1.1952 0.01799 0.01177 -0.0296 0.0117 0.7587
10.000 1.2097 0.01931 0.01323 -0.0277 0.0111 0.7602
10.250 1.2267 0.02029 0.01431 -0.0262 0.0110 0.7618
10.500 1.2465 0.02092 0.01505 -0.0251 0.0108 0.7638
10.750 1.2637 0.02176 0.01600 -0.0236 0.0106 0.7661
11.000 1.2807 0.02257 0.01693 -0.0222 0.0104 0.7688
11.250 1.2955 0.02353 0.01802 -0.0204 0.0102 0.7718
11.500 1.3102 0.02443 0.01903 -0.0187 0.0099 0.7753
11.750 1.3219 0.02551 0.02024 -0.0166 0.0098 0.7796
12.000 1.3338 0.02626 0.02110 -0.0145 0.0095 0.7857
12.250 1.3407 0.02723 0.02220 -0.0115 0.0093 0.7944
12.500 1.3452 0.02829 0.02344 -0.0085 0.0092 0.8133
12.750 1.3525 0.02922 0.02482 -0.0063 0.0091 1.0000
13.000 1.3553 0.03058 0.02627 -0.0036 0.0089 1.0000
13.250 1.3542 0.03230 0.02811 -0.0009 0.0089 1.0000
13.500 1.3519 0.03420 0.03012 0.0015 0.0088 1.0000
13.750 1.3458 0.03658 0.03262 0.0037 0.0087 1.0000
14.000 1.3401 0.03911 0.03530 0.0053 0.0087 1.0000
14.250 1.3279 0.04252 0.03884 0.0064 0.0086 1.0000
14.500 1.3143 0.04649 0.04297 0.0067 0.0085 1.0000
14.750 1.3013 0.05090 0.04753 0.0057 0.0085 1.0000
15.000 1.2868 0.05619 0.05298 0.0035 0.0085 1.0000
15.250 1.2721 0.06232 0.05926 0.0000 0.0085 1.0000
15.500 1.2585 0.06896 0.06606 -0.0043 0.0085 1.0000
15.750 1.2397 0.07702 0.07428 -0.0095 0.0085 1.0000
16.000 1.2191 0.08566 0.08306 -0.0151 0.0085 1.0000
16.250 1.2028 0.09371 0.09125 -0.0201 0.0086 1.0000
16.500 1.1823 0.10264 0.10030 -0.0256 0.0087 1.0000
16.750 1.1573 0.11253 0.11031 -0.0316 0.0087 1.0000
17.000 1.1274 0.12421 0.12217 -0.0387 0.0088 1.0000
17.250 1.0944 0.13712 0.13524 -0.0465 0.0090 1.0000
17.500 1.0418 0.15633 0.15468 -0.0579 0.0092 1.0000
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