NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 500,000 Max Cl/Cd: 70.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722362-il-500000-n5.txt Download as CSV file: xf-nl722362-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5081 0.09133 0.08895 -0.0270 1.0000 0.0072
-9.750 -0.5069 0.08829 0.08593 -0.0283 1.0000 0.0071
-9.500 -0.5126 0.08322 0.08090 -0.0309 1.0000 0.0071
-9.250 -0.5188 0.07838 0.07609 -0.0338 1.0000 0.0071
-9.000 -0.5222 0.07489 0.07263 -0.0364 1.0000 0.0069
-8.750 -0.5442 0.06797 0.06571 -0.0415 0.9967 0.0070
-8.500 -0.5400 0.06234 0.05997 -0.0466 0.9752 0.0068
-8.250 -0.5382 0.05431 0.05172 -0.0515 0.9600 0.0069
-8.000 -0.5344 0.04813 0.04528 -0.0530 0.9485 0.0069
-7.750 -0.5403 0.03976 0.03645 -0.0511 0.9373 0.0072
-7.500 -0.5411 0.03354 0.02977 -0.0480 0.9298 0.0072
-7.250 -0.5441 0.02687 0.02242 -0.0436 0.9233 0.0074
-7.000 -0.5295 0.02496 0.02025 -0.0419 0.9197 0.0076
-6.750 -0.5090 0.02423 0.01940 -0.0410 0.9171 0.0078
-6.500 -0.4908 0.02244 0.01733 -0.0395 0.9146 0.0081
-6.250 -0.4704 0.02113 0.01582 -0.0384 0.9123 0.0085
-6.000 -0.4513 0.01872 0.01299 -0.0366 0.9099 0.0087
-5.750 -0.4291 0.01699 0.01096 -0.0354 0.9078 0.0089
-5.500 -0.4055 0.01573 0.00945 -0.0345 0.9060 0.0093
-5.250 -0.3811 0.01479 0.00833 -0.0337 0.9044 0.0096
-5.000 -0.3564 0.01407 0.00747 -0.0331 0.9029 0.0098
-4.750 -0.3328 0.01325 0.00657 -0.0323 0.9015 0.0101
-4.500 -0.3084 0.01270 0.00599 -0.0317 0.9001 0.0105
-4.250 -0.2834 0.01232 0.00559 -0.0311 0.8987 0.0111
-4.000 -0.2587 0.01194 0.00517 -0.0305 0.8971 0.0118
-3.750 -0.2342 0.01152 0.00471 -0.0298 0.8957 0.0123
-3.500 -0.2097 0.01114 0.00429 -0.0292 0.8943 0.0126
-3.250 -0.1853 0.01074 0.00386 -0.0284 0.8929 0.0131
-3.000 -0.1602 0.01043 0.00355 -0.0279 0.8916 0.0139
-2.750 -0.1347 0.01019 0.00329 -0.0274 0.8901 0.0149
-2.500 -0.1091 0.00998 0.00305 -0.0268 0.8874 0.0162
-2.250 -0.0836 0.00976 0.00280 -0.0262 0.8842 0.0185
-2.000 -0.0591 0.00954 0.00261 -0.0254 0.8795 0.0249
-1.750 -0.0353 0.00924 0.00237 -0.0244 0.8711 0.0476
-1.500 -0.0134 0.00884 0.00212 -0.0229 0.8571 0.1018
-1.250 0.0061 0.00816 0.00186 -0.0212 0.8414 0.2406
-1.000 0.0185 0.00697 0.00166 -0.0183 0.8298 0.5260
-0.750 0.0275 0.00603 0.00160 -0.0141 0.8230 0.7579
-0.500 0.1272 0.00617 0.00223 -0.0289 0.8137 0.9278
-0.250 0.1534 0.00626 0.00226 -0.0283 0.8040 0.9397
0.000 0.1779 0.00635 0.00229 -0.0273 0.7905 0.9496
0.250 0.2117 0.00646 0.00227 -0.0283 0.7369 0.9557
0.500 0.2293 0.00710 0.00226 -0.0259 0.6062 0.9637
0.750 0.2582 0.00764 0.00238 -0.0263 0.5111 0.9673
1.000 0.2844 0.00807 0.00249 -0.0262 0.4376 0.9719
1.250 0.3093 0.00846 0.00259 -0.0257 0.3757 0.9760
1.500 0.3407 0.00880 0.00266 -0.0268 0.3150 0.9779
1.750 0.3714 0.00908 0.00274 -0.0277 0.2704 0.9802
2.000 0.4007 0.00933 0.00282 -0.0282 0.2375 0.9828
2.250 0.4275 0.00955 0.00292 -0.0281 0.2151 0.9856
2.500 0.4587 0.00971 0.00299 -0.0290 0.1978 0.9870
2.750 0.4908 0.00985 0.00308 -0.0301 0.1854 0.9885
3.000 0.5226 0.00999 0.00317 -0.0312 0.1766 0.9903
3.250 0.5545 0.01017 0.00328 -0.0322 0.1674 0.9926
3.500 0.5861 0.01030 0.00341 -0.0332 0.1605 0.9948
3.750 0.6191 0.01045 0.00352 -0.0346 0.1542 0.9964
4.000 0.6507 0.01056 0.00364 -0.0356 0.1500 0.9980
4.250 0.6814 0.01069 0.00378 -0.0364 0.1451 0.9993
4.500 0.7085 0.01086 0.00394 -0.0364 0.1401 1.0000
4.750 0.7316 0.01103 0.00412 -0.0355 0.1367 1.0000
5.000 0.7547 0.01118 0.00428 -0.0347 0.1311 1.0000
5.250 0.7773 0.01138 0.00446 -0.0337 0.1228 1.0000
5.500 0.8003 0.01154 0.00464 -0.0329 0.1151 1.0000
5.750 0.8230 0.01174 0.00483 -0.0319 0.1078 1.0000
6.000 0.8455 0.01195 0.00503 -0.0310 0.0952 1.0000
6.250 0.8666 0.01230 0.00527 -0.0298 0.0773 1.0000
6.500 0.8873 0.01269 0.00560 -0.0286 0.0623 1.0000
6.750 0.9076 0.01314 0.00599 -0.0273 0.0487 1.0000
7.000 0.9274 0.01363 0.00643 -0.0260 0.0363 1.0000
7.250 0.9471 0.01413 0.00689 -0.0246 0.0270 1.0000
7.500 0.9669 0.01461 0.00737 -0.0232 0.0221 1.0000
7.750 0.9865 0.01511 0.00789 -0.0218 0.0193 1.0000
8.000 1.0065 0.01553 0.00839 -0.0204 0.0178 1.0000
8.250 1.0255 0.01606 0.00895 -0.0190 0.0162 1.0000
8.500 1.0441 0.01661 0.00956 -0.0174 0.0150 1.0000
8.750 1.0629 0.01710 0.01013 -0.0159 0.0142 1.0000
9.000 1.0811 0.01762 0.01072 -0.0143 0.0134 1.0000
9.250 1.0984 0.01821 0.01138 -0.0125 0.0128 1.0000
9.500 1.1141 0.01891 0.01215 -0.0106 0.0122 1.0000
9.750 1.1288 0.01965 0.01298 -0.0084 0.0118 1.0000
10.000 1.1438 0.02031 0.01374 -0.0064 0.0115 1.0000
10.250 1.1583 0.02096 0.01449 -0.0042 0.0112 1.0000
10.500 1.1710 0.02170 0.01533 -0.0018 0.0109 1.0000
10.750 1.1827 0.02246 0.01618 0.0007 0.0105 1.0000
11.000 1.1927 0.02327 0.01709 0.0035 0.0103 1.0000
11.250 1.2019 0.02407 0.01800 0.0063 0.0101 1.0000
11.500 1.2073 0.02487 0.01889 0.0099 0.0098 1.0000
11.750 1.2089 0.02569 0.01979 0.0140 0.0097 1.0000
12.000 1.2106 0.02659 0.02078 0.0179 0.0095 1.0000
12.250 1.2117 0.02763 0.02192 0.0215 0.0094 1.0000
12.500 1.2084 0.02905 0.02343 0.0253 0.0092 1.0000
12.750 1.2080 0.03042 0.02492 0.0285 0.0090 1.0000
13.000 1.2089 0.03179 0.02642 0.0312 0.0090 1.0000
13.250 1.2082 0.03340 0.02817 0.0337 0.0088 1.0000
13.500 1.2076 0.03508 0.03001 0.0359 0.0087 1.0000
13.750 1.2042 0.03711 0.03217 0.0380 0.0087 1.0000
14.000 1.2008 0.03929 0.03450 0.0395 0.0086 1.0000
14.250 1.1935 0.04205 0.03742 0.0407 0.0084 1.0000
14.500 1.1869 0.04505 0.04057 0.0411 0.0084 1.0000
14.750 1.1764 0.04893 0.04461 0.0405 0.0084 1.0000
15.000 1.1641 0.05369 0.04954 0.0386 0.0083 1.0000
15.250 1.1492 0.05960 0.05562 0.0355 0.0083 1.0000
15.500 1.1333 0.06637 0.06257 0.0314 0.0083 1.0000
15.750 1.1167 0.07351 0.06985 0.0272 0.0083 1.0000
16.000 1.0934 0.08187 0.07836 0.0226 0.0083 1.0000
16.250 1.0748 0.08937 0.08598 0.0186 0.0083 1.0000
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