NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.93 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722362-il-1000000.txt Download as CSV file: xf-nl722362-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5036 0.08037 0.07876 -0.0332 1.0000 0.0097
-9.000 -0.5082 0.07603 0.07445 -0.0364 1.0000 0.0097
-8.750 -0.5263 0.06981 0.06824 -0.0416 1.0000 0.0097
-7.500 -0.5084 0.03998 0.03742 -0.0533 0.9372 0.0101
-7.250 -0.4986 0.03798 0.03528 -0.0518 0.9318 0.0103
-7.000 -0.4873 0.03582 0.03297 -0.0503 0.9275 0.0105
-6.750 -0.4746 0.03370 0.03069 -0.0487 0.9239 0.0109
-6.500 -0.4623 0.03096 0.02773 -0.0465 0.9205 0.0112
-5.250 -0.3829 0.01637 0.01142 -0.0346 0.9083 0.0121
-5.000 -0.3598 0.01438 0.00916 -0.0334 0.9068 0.0116
-4.750 -0.3350 0.01303 0.00764 -0.0326 0.9054 0.0116
-4.500 -0.3100 0.01203 0.00652 -0.0318 0.9043 0.0119
-4.250 -0.2848 0.01140 0.00581 -0.0312 0.9031 0.0123
-4.000 -0.2595 0.01094 0.00529 -0.0306 0.9017 0.0126
-3.750 -0.2344 0.01054 0.00484 -0.0300 0.8999 0.0128
-3.500 -0.2119 0.00983 0.00409 -0.0288 0.8983 0.0131
-3.250 -0.1885 0.00937 0.00362 -0.0279 0.8953 0.0138
-3.000 -0.1632 0.00909 0.00334 -0.0273 0.8933 0.0146
-2.750 -0.1384 0.00879 0.00300 -0.0266 0.8902 0.0150
-2.500 -0.1136 0.00857 0.00272 -0.0257 0.8845 0.0160
-2.250 -0.0902 0.00821 0.00232 -0.0244 0.8754 0.0172
-2.000 -0.0659 0.00797 0.00204 -0.0234 0.8659 0.0196
-1.750 -0.0412 0.00768 0.00176 -0.0225 0.8579 0.0303
-1.500 -0.0194 0.00707 0.00157 -0.0213 0.8535 0.1527
-1.250 -0.0017 0.00612 0.00140 -0.0196 0.8499 0.3883
-1.000 0.0147 0.00530 0.00129 -0.0174 0.8458 0.5985
-0.750 0.0330 0.00484 0.00122 -0.0152 0.8413 0.7155
-0.500 0.1026 0.00450 0.00160 -0.0239 0.8369 0.9250
-0.250 0.1326 0.00486 0.00195 -0.0238 0.8304 0.9529
0.000 0.1682 0.00513 0.00216 -0.0251 0.8234 0.9632
0.250 0.2090 0.00521 0.00221 -0.0279 0.8136 0.9653
0.500 0.2452 0.00527 0.00223 -0.0296 0.8005 0.9678
0.750 0.2784 0.00537 0.00226 -0.0306 0.7761 0.9720
1.000 0.3019 0.00608 0.00228 -0.0296 0.6058 0.9770
1.250 0.3346 0.00666 0.00239 -0.0310 0.4883 0.9796
1.500 0.3643 0.00712 0.00248 -0.0317 0.3983 0.9828
1.750 0.3913 0.00752 0.00260 -0.0317 0.3293 0.9864
2.000 0.4257 0.00781 0.00261 -0.0335 0.2673 0.9877
2.250 0.4588 0.00805 0.00265 -0.0349 0.2239 0.9893
2.500 0.4910 0.00824 0.00271 -0.0361 0.1963 0.9912
2.750 0.5226 0.00840 0.00277 -0.0371 0.1799 0.9934
3.000 0.5542 0.00853 0.00284 -0.0380 0.1695 0.9952
3.250 0.5877 0.00858 0.00287 -0.0394 0.1635 0.9964
3.500 0.6203 0.00865 0.00292 -0.0407 0.1580 0.9978
3.750 0.6527 0.00876 0.00300 -0.0418 0.1520 0.9992
4.000 0.6824 0.00882 0.00307 -0.0424 0.1494 1.0000
4.250 0.7061 0.00893 0.00318 -0.0416 0.1458 1.0000
4.500 0.7291 0.00912 0.00333 -0.0407 0.1387 1.0000
4.750 0.7532 0.00919 0.00342 -0.0400 0.1351 1.0000
5.000 0.7768 0.00931 0.00355 -0.0393 0.1308 1.0000
5.250 0.7998 0.00951 0.00371 -0.0384 0.1242 1.0000
5.500 0.8239 0.00958 0.00382 -0.0377 0.1201 1.0000
5.750 0.8470 0.00976 0.00396 -0.0368 0.1123 1.0000
6.000 0.8705 0.00990 0.00410 -0.0360 0.1028 1.0000
6.250 0.8926 0.01017 0.00427 -0.0350 0.0851 1.0000
6.500 0.9134 0.01057 0.00457 -0.0339 0.0669 1.0000
6.750 0.9341 0.01099 0.00491 -0.0326 0.0503 1.0000
7.000 0.9532 0.01160 0.00538 -0.0311 0.0302 1.0000
7.250 0.9735 0.01207 0.00582 -0.0298 0.0228 1.0000
7.500 0.9937 0.01256 0.00631 -0.0284 0.0192 1.0000
7.750 1.0147 0.01292 0.00672 -0.0272 0.0177 1.0000
8.000 1.0347 0.01340 0.00722 -0.0258 0.0163 1.0000
8.250 1.0538 0.01396 0.00785 -0.0243 0.0151 1.0000
8.500 1.0739 0.01438 0.00832 -0.0229 0.0143 1.0000
8.750 1.0934 0.01484 0.00885 -0.0214 0.0138 1.0000
9.000 1.1124 0.01534 0.00939 -0.0199 0.0132 1.0000
9.250 1.1297 0.01596 0.01007 -0.0182 0.0126 1.0000
9.500 1.1423 0.01698 0.01120 -0.0156 0.0120 1.0000
9.750 1.1585 0.01762 0.01192 -0.0136 0.0117 1.0000
10.000 1.1742 0.01824 0.01262 -0.0116 0.0115 1.0000
10.250 1.1907 0.01876 0.01321 -0.0097 0.0112 1.0000
10.500 1.2057 0.01936 0.01388 -0.0077 0.0109 1.0000
10.750 1.2185 0.02008 0.01468 -0.0052 0.0106 1.0000
11.000 1.2300 0.02083 0.01553 -0.0026 0.0104 1.0000
11.250 1.2410 0.02157 0.01633 0.0001 0.0101 1.0000
11.500 1.2498 0.02237 0.01721 0.0031 0.0099 1.0000
11.750 1.2557 0.02321 0.01813 0.0066 0.0097 1.0000
12.000 1.2538 0.02402 0.01901 0.0115 0.0096 1.0000
12.250 1.2525 0.02488 0.01996 0.0161 0.0096 1.0000
12.500 1.2464 0.02618 0.02136 0.0210 0.0094 1.0000
12.750 1.2393 0.02777 0.02307 0.0255 0.0092 1.0000
13.000 1.2395 0.02900 0.02441 0.0287 0.0092 1.0000
13.250 1.2261 0.03145 0.02701 0.0329 0.0091 1.0000
13.500 1.2157 0.03389 0.02961 0.0363 0.0090 1.0000
13.750 1.2115 0.03590 0.03175 0.0386 0.0090 1.0000
14.000 1.2123 0.03753 0.03349 0.0403 0.0090 1.0000
14.250 1.2064 0.03996 0.03607 0.0418 0.0089 1.0000
14.500 1.2046 0.04218 0.03840 0.0426 0.0089 1.0000
14.750 1.1949 0.04554 0.04190 0.0430 0.0089 1.0000
15.000 1.1832 0.04962 0.04613 0.0422 0.0089 1.0000
15.250 1.1698 0.05452 0.05119 0.0404 0.0089 1.0000
15.500 1.1561 0.06011 0.05693 0.0374 0.0088 1.0000
15.750 1.1460 0.06570 0.06266 0.0340 0.0088 1.0000
16.000 1.1152 0.07483 0.07196 0.0290 0.0089 1.0000
16.250 1.1106 0.08027 0.07751 0.0252 0.0088 1.0000
16.500 1.0779 0.08999 0.08737 0.0202 0.0089 1.0000
16.750 1.0633 0.09709 0.09458 0.0161 0.0089 1.0000
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Polar data table (+)
Polar graphs
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