NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 100,000 Max Cl/Cd: 41.39 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722343-il-100000-n5.txt Download as CSV file: xf-nl722343-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5133 0.09195 0.08686 -0.0337 1.0000 0.0563
-8.750 -0.5294 0.08772 0.08267 -0.0375 1.0000 0.0565
-8.500 -0.5483 0.08445 0.07937 -0.0391 1.0000 0.0567
-8.250 -0.5593 0.08120 0.07603 -0.0396 1.0000 0.0569
-7.750 -0.5423 0.07265 0.06773 -0.0367 1.0000 0.0597
-7.250 -0.5514 0.06111 0.05580 -0.0370 1.0000 0.0345
-7.000 -0.5587 0.05478 0.04892 -0.0358 1.0000 0.0284
-6.750 -0.5521 0.05189 0.04602 -0.0344 1.0000 0.0278
-6.500 -0.5465 0.04870 0.04270 -0.0329 1.0000 0.0273
-6.250 -0.5391 0.04553 0.03931 -0.0314 1.0000 0.0266
-6.000 -0.5296 0.04229 0.03579 -0.0298 1.0000 0.0260
-5.750 -0.5177 0.03913 0.03227 -0.0283 1.0000 0.0254
-5.500 -0.5034 0.03601 0.02874 -0.0267 1.0000 0.0248
-5.250 -0.4868 0.03317 0.02548 -0.0253 1.0000 0.0246
-5.000 -0.4682 0.03070 0.02261 -0.0239 1.0000 0.0245
-4.750 -0.4482 0.02860 0.02014 -0.0226 1.0000 0.0247
-4.500 -0.4274 0.02700 0.01824 -0.0215 1.0000 0.0260
-4.250 -0.4052 0.02546 0.01632 -0.0203 1.0000 0.0275
-4.000 -0.3824 0.02396 0.01452 -0.0191 1.0000 0.0281
-3.750 -0.3595 0.02261 0.01298 -0.0180 1.0000 0.0286
-3.500 -0.3371 0.02130 0.01164 -0.0170 1.0000 0.0294
-3.250 -0.3148 0.02031 0.01062 -0.0161 1.0000 0.0306
-3.000 -0.2926 0.01949 0.00978 -0.0151 1.0000 0.0324
-2.750 -0.2704 0.01887 0.00907 -0.0141 1.0000 0.0355
-2.500 -0.2486 0.01811 0.00835 -0.0132 1.0000 0.0390
-2.250 -0.2173 0.01754 0.00768 -0.0141 0.9969 0.0438
-2.000 -0.1858 0.01704 0.00716 -0.0150 0.9936 0.0554
-1.750 -0.1556 0.01616 0.00664 -0.0159 0.9900 0.1180
-1.500 -0.1410 0.01470 0.00759 -0.0131 0.9860 0.7318
-1.250 -0.1265 0.01485 0.00792 -0.0084 0.9800 0.8047
-1.000 -0.1095 0.01483 0.00799 -0.0044 0.9744 0.8542
-0.750 -0.0804 0.01480 0.00783 -0.0046 0.9686 0.8660
-0.500 -0.0440 0.01484 0.00770 -0.0066 0.9629 0.8679
-0.250 -0.0076 0.01485 0.00759 -0.0086 0.9564 0.8694
0.000 0.0312 0.01484 0.00748 -0.0109 0.9487 0.8708
0.250 0.0718 0.01474 0.00730 -0.0135 0.9375 0.8721
0.500 0.1303 0.01435 0.00682 -0.0189 0.9185 0.8715
0.750 0.1808 0.01390 0.00631 -0.0225 0.8970 0.8714
1.000 0.2186 0.01367 0.00605 -0.0240 0.8816 0.8726
1.250 0.2526 0.01349 0.00588 -0.0249 0.8668 0.8745
1.500 0.2836 0.01333 0.00574 -0.0252 0.8490 0.8768
1.750 0.3153 0.01317 0.00560 -0.0256 0.8279 0.8788
2.000 0.3463 0.01301 0.00544 -0.0257 0.8002 0.8809
2.250 0.3777 0.01286 0.00530 -0.0259 0.7605 0.8830
2.500 0.4138 0.01273 0.00497 -0.0266 0.6751 0.8846
2.750 0.4456 0.01310 0.00471 -0.0265 0.5509 0.8867
3.000 0.4677 0.01374 0.00485 -0.0253 0.4500 0.8905
3.250 0.4901 0.01434 0.00511 -0.0245 0.3743 0.8954
3.500 0.5142 0.01489 0.00539 -0.0240 0.3212 0.9009
3.750 0.5398 0.01537 0.00571 -0.0238 0.2860 0.9073
4.000 0.5666 0.01581 0.00606 -0.0238 0.2631 0.9147
4.250 0.5949 0.01626 0.00649 -0.0242 0.2466 0.9243
4.500 0.6251 0.01671 0.00694 -0.0250 0.2328 0.9373
4.750 0.6568 0.01719 0.00742 -0.0261 0.2211 0.9604
5.000 0.6846 0.01770 0.00792 -0.0265 0.2112 1.0000
5.250 0.7102 0.01818 0.00843 -0.0264 0.2019 1.0000
5.500 0.7355 0.01872 0.00898 -0.0263 0.1937 1.0000
5.750 0.7609 0.01926 0.00954 -0.0261 0.1855 1.0000
6.000 0.7863 0.01981 0.01019 -0.0260 0.1770 1.0000
6.250 0.8110 0.02040 0.01078 -0.0257 0.1686 1.0000
6.500 0.8361 0.02092 0.01146 -0.0254 0.1590 1.0000
6.750 0.8601 0.02144 0.01209 -0.0251 0.1484 1.0000
7.000 0.8832 0.02182 0.01256 -0.0246 0.1345 1.0000
7.250 0.9065 0.02212 0.01300 -0.0241 0.1185 1.0000
7.500 0.9302 0.02248 0.01350 -0.0237 0.1008 1.0000
7.750 0.9531 0.02303 0.01407 -0.0231 0.0819 1.0000
8.000 0.9734 0.02404 0.01497 -0.0223 0.0658 1.0000
8.250 0.9922 0.02534 0.01625 -0.0213 0.0540 1.0000
8.500 1.0106 0.02666 0.01772 -0.0202 0.0468 1.0000
8.750 1.0276 0.02811 0.01929 -0.0188 0.0422 1.0000
9.000 1.0444 0.02947 0.02077 -0.0176 0.0383 1.0000
9.250 1.0591 0.03103 0.02244 -0.0161 0.0356 1.0000
9.500 1.0741 0.03266 0.02432 -0.0146 0.0337 1.0000
9.750 1.0878 0.03438 0.02625 -0.0131 0.0322 1.0000
10.000 1.0999 0.03611 0.02812 -0.0115 0.0308 1.0000
10.250 1.1100 0.03797 0.03005 -0.0098 0.0296 1.0000
10.500 1.1186 0.04012 0.03249 -0.0080 0.0285 1.0000
10.750 1.1243 0.04233 0.03503 -0.0059 0.0274 1.0000
11.000 1.1255 0.04463 0.03760 -0.0035 0.0266 1.0000
11.250 1.1238 0.04715 0.04038 -0.0010 0.0261 1.0000
11.500 1.1188 0.04990 0.04340 0.0012 0.0257 1.0000
11.750 1.1107 0.05294 0.04668 0.0029 0.0254 1.0000
12.000 1.0994 0.05647 0.05045 0.0039 0.0252 1.0000
12.250 1.0846 0.06061 0.05484 0.0040 0.0251 1.0000
12.500 1.0659 0.06576 0.06024 0.0025 0.0252 1.0000
12.750 1.0419 0.07260 0.06733 -0.0012 0.0253 1.0000
13.000 1.0101 0.08264 0.07761 -0.0086 0.0257 1.0000
13.250 0.9582 0.10004 0.09522 -0.0215 0.0267 1.0000
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Polar data table (+)
Polar graphs
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