NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 50,000 Max Cl/Cd: 28.51 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722362-il-50000-n5.txt Download as CSV file: xf-nl722362-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-62 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4921 0.11030 0.10310 -0.0200 1.0000 0.1264
-9.500 -0.4916 0.10704 0.09990 -0.0210 1.0000 0.1309
-9.250 -0.5225 0.10495 0.09799 -0.0270 1.0000 0.1358
-9.000 -0.4070 0.08614 0.07948 -0.0313 1.0000 0.0699
-8.750 -0.4220 0.08029 0.07366 -0.0351 1.0000 0.0610
-8.250 -0.5264 0.08221 0.07526 -0.0348 1.0000 0.0607
-8.000 -0.5315 0.07872 0.07181 -0.0340 1.0000 0.0588
-7.750 -0.5403 0.07513 0.06822 -0.0330 1.0000 0.0566
-7.250 -0.5652 0.06781 0.06056 -0.0294 1.0000 0.0501
-7.000 -0.5664 0.06475 0.05744 -0.0270 1.0000 0.0492
-6.750 -0.5681 0.06179 0.05438 -0.0245 1.0000 0.0483
-6.500 -0.5691 0.05879 0.05122 -0.0218 1.0000 0.0473
-6.250 -0.5688 0.05570 0.04791 -0.0190 1.0000 0.0463
-6.000 -0.5665 0.05261 0.04455 -0.0161 1.0000 0.0454
-5.750 -0.5619 0.04960 0.04120 -0.0133 1.0000 0.0444
-5.500 -0.5551 0.04661 0.03782 -0.0104 1.0000 0.0436
-5.250 -0.5455 0.04377 0.03456 -0.0076 1.0000 0.0429
-5.000 -0.5334 0.04119 0.03155 -0.0050 1.0000 0.0425
-4.750 -0.5193 0.03881 0.02878 -0.0027 1.0000 0.0426
-4.500 -0.5036 0.03683 0.02650 -0.0008 1.0000 0.0442
-4.250 -0.4860 0.03494 0.02428 0.0011 1.0000 0.0459
-4.000 -0.4663 0.03307 0.02202 0.0030 1.0000 0.0474
-3.750 -0.4447 0.03129 0.01988 0.0045 1.0000 0.0483
-3.500 -0.4215 0.02968 0.01795 0.0059 1.0000 0.0492
-3.250 -0.3968 0.02824 0.01618 0.0071 1.0000 0.0507
-3.000 -0.3727 0.02684 0.01478 0.0080 1.0000 0.0546
-2.750 -0.3479 0.02586 0.01365 0.0089 1.0000 0.0594
-2.500 -0.3221 0.02486 0.01245 0.0097 1.0000 0.0644
-2.000 -0.1198 0.01952 0.01040 -0.0161 1.0000 1.0000
-1.750 -0.1074 0.01947 0.01004 -0.0136 1.0000 1.0000
-1.500 -0.0941 0.01945 0.00974 -0.0113 1.0000 1.0000
-1.250 -0.0801 0.01945 0.00951 -0.0090 1.0000 1.0000
-1.000 -0.0655 0.01948 0.00930 -0.0069 1.0000 1.0000
-0.750 -0.0504 0.01953 0.00916 -0.0048 1.0000 1.0000
-0.500 -0.0349 0.01961 0.00907 -0.0029 1.0000 1.0000
-0.250 -0.0191 0.01971 0.00902 -0.0010 1.0000 1.0000
0.000 -0.0030 0.01983 0.00901 0.0009 1.0000 1.0000
0.250 0.0132 0.01997 0.00904 0.0026 1.0000 1.0000
0.500 0.0297 0.02014 0.00911 0.0043 1.0000 1.0000
0.750 0.0461 0.02033 0.00924 0.0060 1.0000 1.0000
1.000 0.0627 0.02056 0.00940 0.0076 1.0000 1.0000
1.250 0.1013 0.02097 0.00979 0.0046 0.9918 1.0000
1.500 0.1674 0.02151 0.01035 -0.0036 0.9725 1.0000
1.750 0.2503 0.02160 0.01053 -0.0142 0.9404 1.0000
2.000 0.3229 0.02134 0.01040 -0.0222 0.9114 1.0000
2.250 0.3786 0.02100 0.01023 -0.0268 0.8867 1.0000
2.500 0.4154 0.02066 0.01002 -0.0276 0.8590 1.0000
2.750 0.4446 0.02032 0.00981 -0.0269 0.8269 1.0000
3.000 0.4580 0.02017 0.00981 -0.0234 0.7839 1.0000
3.250 0.4681 0.02002 0.00976 -0.0192 0.7160 1.0000
3.500 0.5439 0.01908 0.00800 -0.0241 0.5335 1.0000
3.750 0.5603 0.01996 0.00828 -0.0214 0.4391 1.0000
4.000 0.5766 0.02084 0.00878 -0.0192 0.3836 1.0000
4.250 0.5955 0.02165 0.00935 -0.0176 0.3470 1.0000
4.500 0.6159 0.02242 0.00996 -0.0164 0.3209 1.0000
4.750 0.6384 0.02315 0.01061 -0.0154 0.3008 1.0000
5.000 0.6625 0.02387 0.01135 -0.0147 0.2848 1.0000
5.250 0.6875 0.02459 0.01208 -0.0142 0.2705 1.0000
5.500 0.7133 0.02533 0.01285 -0.0138 0.2573 1.0000
5.750 0.7385 0.02607 0.01372 -0.0134 0.2446 1.0000
6.000 0.7632 0.02686 0.01465 -0.0128 0.2325 1.0000
6.250 0.7868 0.02770 0.01562 -0.0121 0.2205 1.0000
6.500 0.8096 0.02860 0.01661 -0.0112 0.2090 1.0000
6.750 0.8315 0.02952 0.01762 -0.0103 0.1975 1.0000
7.000 0.8511 0.03045 0.01878 -0.0090 0.1844 1.0000
7.250 0.8696 0.03144 0.01998 -0.0075 0.1709 1.0000
7.500 0.8867 0.03246 0.02122 -0.0059 0.1569 1.0000
7.750 0.9010 0.03333 0.02224 -0.0039 0.1417 1.0000
8.000 0.9136 0.03411 0.02316 -0.0016 0.1264 1.0000
8.250 0.9253 0.03494 0.02411 0.0007 0.1119 1.0000
8.500 0.9369 0.03603 0.02540 0.0030 0.0982 1.0000
8.750 0.9484 0.03723 0.02676 0.0053 0.0872 1.0000
9.000 0.9591 0.03856 0.02819 0.0076 0.0785 1.0000
9.250 0.9694 0.04076 0.03069 0.0098 0.0714 1.0000
9.500 0.9780 0.04213 0.03197 0.0121 0.0665 1.0000
9.750 0.9833 0.04498 0.03535 0.0147 0.0619 1.0000
10.000 0.9875 0.04744 0.03807 0.0172 0.0591 1.0000
10.250 0.9916 0.04953 0.04027 0.0195 0.0569 1.0000
10.500 0.9894 0.05238 0.04334 0.0222 0.0553 1.0000
10.750 0.9762 0.05579 0.04716 0.0257 0.0541 1.0000
11.000 0.9588 0.05927 0.05093 0.0289 0.0534 1.0000
11.250 0.9382 0.06320 0.05511 0.0310 0.0530 1.0000
11.500 0.9139 0.06796 0.06009 0.0317 0.0530 1.0000
11.750 0.8864 0.07391 0.06622 0.0304 0.0535 1.0000
12.000 0.8570 0.08142 0.07381 0.0266 0.0543 1.0000
12.250 0.8296 0.09046 0.08290 0.0211 0.0552 1.0000
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Polar data table (+)
Polar graphs
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