NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 100,000 Max Cl/Cd: 39.78 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722362-il-100000-n5.txt Download as CSV file: xf-nl722362-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4929 0.09075 0.08575 -0.0304 1.0000 0.0543
-8.750 -0.4964 0.08681 0.08187 -0.0321 1.0000 0.0551
-8.500 -0.5038 0.08285 0.07798 -0.0345 1.0000 0.0553
-8.250 -0.5160 0.07933 0.07451 -0.0351 1.0000 0.0555
-8.000 -0.5296 0.07634 0.07156 -0.0339 1.0000 0.0558
-7.750 -0.5420 0.07333 0.06855 -0.0324 1.0000 0.0560
-7.500 -0.5541 0.07063 0.06583 -0.0300 1.0000 0.0564
-7.250 -0.5655 0.06796 0.06312 -0.0272 1.0000 0.0564
-7.000 -0.5870 0.06202 0.05680 -0.0238 1.0000 0.0421
-6.500 -0.5976 0.05185 0.04587 -0.0159 1.0000 0.0257
-6.250 -0.5943 0.04916 0.04307 -0.0132 1.0000 0.0253
-6.000 -0.5903 0.04635 0.04005 -0.0104 1.0000 0.0250
-5.750 -0.5842 0.04364 0.03711 -0.0076 1.0000 0.0247
-5.500 -0.5766 0.04081 0.03396 -0.0047 1.0000 0.0244
-5.250 -0.5669 0.03805 0.03084 -0.0019 1.0000 0.0243
-5.000 -0.5502 0.03535 0.02770 -0.0001 0.9987 0.0246
-4.750 -0.5296 0.03283 0.02450 0.0016 0.9967 0.0257
-4.500 -0.5075 0.03045 0.02176 0.0024 0.9950 0.0262
-4.250 -0.4840 0.02842 0.01936 0.0034 0.9933 0.0263
-4.000 -0.4601 0.02664 0.01728 0.0042 0.9918 0.0266
-3.750 -0.4344 0.02513 0.01555 0.0047 0.9902 0.0270
-3.500 -0.4071 0.02384 0.01408 0.0049 0.9885 0.0276
-3.250 -0.3789 0.02267 0.01276 0.0050 0.9868 0.0287
-3.000 -0.3500 0.02184 0.01177 0.0049 0.9850 0.0317
-2.750 -0.3254 0.02089 0.01081 0.0055 0.9827 0.0336
-2.500 -0.3005 0.02008 0.01001 0.0060 0.9801 0.0359
-2.250 -0.2742 0.01948 0.00931 0.0063 0.9774 0.0385
-2.000 -0.2460 0.01892 0.00870 0.0061 0.9747 0.0444
-1.750 -0.2191 0.01844 0.00819 0.0063 0.9717 0.0545
-1.500 -0.0728 0.01557 0.00878 -0.0161 0.9927 1.0000
-1.250 -0.0425 0.01561 0.00860 -0.0171 0.9886 1.0000
-1.000 -0.0097 0.01570 0.00849 -0.0185 0.9849 1.0000
-0.750 0.0199 0.01572 0.00836 -0.0193 0.9797 1.0000
-0.500 0.0560 0.01581 0.00832 -0.0214 0.9748 1.0000
-0.250 0.0907 0.01584 0.00824 -0.0231 0.9678 1.0000
0.000 0.1472 0.01576 0.00806 -0.0289 0.9570 1.0000
0.250 0.2617 0.01470 0.00691 -0.0449 0.9277 1.0000
0.500 0.3050 0.01434 0.00652 -0.0475 0.9121 1.0000
0.750 0.3393 0.01414 0.00630 -0.0485 0.8998 1.0000
1.000 0.3663 0.01400 0.00616 -0.0480 0.8859 1.0000
1.250 0.3924 0.01385 0.00602 -0.0472 0.8701 1.0000
1.500 0.4130 0.01375 0.00595 -0.0453 0.8508 1.0000
1.750 0.4339 0.01363 0.00585 -0.0435 0.8278 1.0000
2.000 0.4523 0.01355 0.00580 -0.0411 0.7980 1.0000
2.250 0.4648 0.01357 0.00586 -0.0378 0.7371 1.0000
2.500 0.5041 0.01324 0.00468 -0.0377 0.5718 1.0000
2.750 0.5201 0.01395 0.00479 -0.0352 0.4606 1.0000
3.000 0.5371 0.01461 0.00502 -0.0331 0.3811 1.0000
3.250 0.5560 0.01518 0.00529 -0.0315 0.3265 1.0000
3.500 0.5760 0.01569 0.00559 -0.0301 0.2912 1.0000
3.750 0.5967 0.01614 0.00594 -0.0288 0.2684 1.0000
4.000 0.6175 0.01658 0.00631 -0.0275 0.2521 1.0000
4.250 0.6384 0.01702 0.00669 -0.0263 0.2392 1.0000
4.500 0.6592 0.01750 0.00713 -0.0250 0.2281 1.0000
4.750 0.6807 0.01791 0.00757 -0.0238 0.2180 1.0000
5.000 0.7017 0.01839 0.00803 -0.0226 0.2092 1.0000
5.250 0.7230 0.01885 0.00852 -0.0215 0.2007 1.0000
5.500 0.7443 0.01934 0.00907 -0.0203 0.1929 1.0000
5.750 0.7655 0.01982 0.00959 -0.0192 0.1849 1.0000
6.000 0.7868 0.02034 0.01018 -0.0180 0.1772 1.0000
6.250 0.8074 0.02085 0.01073 -0.0168 0.1690 1.0000
6.500 0.8284 0.02135 0.01140 -0.0156 0.1602 1.0000
6.750 0.8480 0.02187 0.01195 -0.0143 0.1511 1.0000
7.000 0.8668 0.02223 0.01242 -0.0128 0.1388 1.0000
7.250 0.8852 0.02252 0.01283 -0.0113 0.1245 1.0000
7.500 0.9047 0.02285 0.01333 -0.0099 0.1090 1.0000
7.750 0.9242 0.02323 0.01383 -0.0085 0.0909 1.0000
8.000 0.9414 0.02392 0.01448 -0.0069 0.0742 1.0000
8.250 0.9567 0.02496 0.01552 -0.0050 0.0604 1.0000
8.500 0.9704 0.02619 0.01679 -0.0029 0.0518 1.0000
8.750 0.9826 0.02747 0.01809 -0.0006 0.0459 1.0000
9.000 0.9959 0.02865 0.01944 0.0016 0.0411 1.0000
9.250 1.0059 0.02999 0.02085 0.0041 0.0383 1.0000
9.500 1.0161 0.03142 0.02249 0.0067 0.0363 1.0000
9.750 1.0258 0.03285 0.02411 0.0092 0.0342 1.0000
10.000 1.0340 0.03421 0.02560 0.0118 0.0324 1.0000
10.250 1.0401 0.03569 0.02717 0.0145 0.0312 1.0000
10.500 1.0452 0.03739 0.02904 0.0174 0.0300 1.0000
10.750 1.0480 0.03914 0.03106 0.0205 0.0289 1.0000
11.000 1.0483 0.04098 0.03313 0.0239 0.0282 1.0000
11.250 1.0467 0.04299 0.03537 0.0270 0.0277 1.0000
11.500 1.0432 0.04517 0.03777 0.0300 0.0272 1.0000
11.750 1.0379 0.04755 0.04037 0.0327 0.0267 1.0000
12.000 1.0306 0.05017 0.04320 0.0349 0.0264 1.0000
12.250 1.0210 0.05313 0.04638 0.0367 0.0262 1.0000
12.500 1.0085 0.05654 0.05000 0.0377 0.0260 1.0000
12.750 0.9938 0.06048 0.05414 0.0379 0.0258 1.0000
13.000 0.9742 0.06560 0.05951 0.0365 0.0260 1.0000
13.250 0.9504 0.07227 0.06640 0.0330 0.0260 1.0000
13.500 0.9152 0.08279 0.07718 0.0256 0.0265 1.0000
13.750 0.8534 0.10196 0.09655 0.0125 0.0278 1.0000
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Polar data table (+)
Polar graphs
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