Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=200,000 Ncrit=1
| Details | Polar file |
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Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Reynolds number: 200,000 Max Cl/Cd: 34.63 at α=6.5° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-120-050-gn-200000-n1.txt Download as CSV file: xf-cp-120-050-gn-200000-n1.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=12% T=5% R=1.1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.1057 0.11103 0.10571 -0.1587 0.8663 0.0140
-10.500 0.1144 0.10884 0.10350 -0.1596 0.8630 0.0142
-10.250 0.1241 0.10655 0.10119 -0.1608 0.8598 0.0145
-10.000 0.1351 0.10422 0.09885 -0.1623 0.8565 0.0149
-9.750 0.1476 0.10201 0.09661 -0.1640 0.8535 0.0155
-9.500 0.1563 0.09998 0.09458 -0.1647 0.8497 0.0157
-9.250 0.1648 0.09802 0.09261 -0.1653 0.8461 0.0159
-9.000 0.1743 0.09598 0.09056 -0.1661 0.8422 0.0161
-8.750 0.1849 0.09388 0.08844 -0.1673 0.8385 0.0163
-8.500 0.1949 0.09190 0.08644 -0.1681 0.8350 0.0164
-8.250 0.2018 0.09013 0.08467 -0.1681 0.8310 0.0165
-8.000 0.2086 0.08815 0.08269 -0.1683 0.8269 0.0172
-7.750 0.2182 0.08639 0.08092 -0.1688 0.8228 0.0176
-7.500 0.2277 0.08459 0.07911 -0.1694 0.8189 0.0180
-7.250 0.2329 0.08305 0.07757 -0.1687 0.8146 0.0183
-7.000 0.2387 0.08149 0.07602 -0.1682 0.8103 0.0184
-6.750 0.2455 0.07986 0.07438 -0.1680 0.8060 0.0186
-6.500 0.2514 0.07829 0.07281 -0.1675 0.8015 0.0187
-6.250 0.2530 0.07703 0.07157 -0.1658 0.7969 0.0189
-6.000 0.2542 0.07574 0.07030 -0.1641 0.7921 0.0191
-5.750 0.2554 0.07436 0.06892 -0.1625 0.7872 0.0195
-5.500 0.2507 0.07343 0.06802 -0.1592 0.7820 0.0200
-5.250 0.2496 0.07235 0.06697 -0.1568 0.7771 0.0203
-5.000 0.2525 0.07104 0.06566 -0.1554 0.7724 0.0206
-4.750 0.2565 0.06966 0.06428 -0.1543 0.7677 0.0207
-4.500 0.2573 0.06845 0.06309 -0.1523 0.7627 0.0209
-4.250 0.2610 0.06709 0.06175 -0.1511 0.7582 0.0210
-4.000 0.2693 0.06553 0.06018 -0.1509 0.7538 0.0211
-3.750 0.2754 0.06407 0.05872 -0.1501 0.7491 0.0214
-3.500 0.2820 0.06261 0.05728 -0.1494 0.7445 0.0216
-3.250 0.2924 0.06089 0.05555 -0.1497 0.7401 0.0221
-3.000 0.3073 0.05908 0.05371 -0.1508 0.7363 0.0228
-2.750 0.3194 0.05755 0.05219 -0.1510 0.7317 0.0232
-2.500 0.3337 0.05592 0.05056 -0.1517 0.7274 0.0234
-2.250 0.3515 0.05419 0.04881 -0.1531 0.7236 0.0236
-2.000 0.3733 0.05233 0.04691 -0.1552 0.7199 0.0238
-1.750 0.3947 0.05052 0.04508 -0.1572 0.7159 0.0241
-1.500 0.4170 0.04872 0.04325 -0.1593 0.7119 0.0246
-1.250 0.4433 0.04674 0.04124 -0.1622 0.7083 0.0255
-1.000 0.4710 0.04503 0.03950 -0.1650 0.7047 0.0260
-0.750 0.5016 0.04323 0.03764 -0.1683 0.7013 0.0263
-0.500 0.5299 0.04160 0.03598 -0.1709 0.6975 0.0265
-0.250 0.5605 0.03995 0.03429 -0.1740 0.6940 0.0269
0.000 0.5934 0.03828 0.03257 -0.1773 0.6904 0.0274
0.500 0.6635 0.03503 0.02920 -0.1844 0.6835 0.0290
0.750 0.6958 0.03369 0.02782 -0.1870 0.6800 0.0293
1.000 0.7290 0.03238 0.02646 -0.1897 0.6764 0.0296
1.250 0.7632 0.03108 0.02511 -0.1924 0.6726 0.0300
1.500 0.7986 0.02971 0.02358 -0.1952 0.6587 0.0312
1.750 0.8258 0.02879 0.02235 -0.1960 0.6193 0.0319
2.000 0.8273 0.02912 0.02214 -0.1915 0.5412 0.0321
2.250 0.7991 0.03126 0.02353 -0.1819 0.4084 0.0321
2.500 0.7755 0.03367 0.02515 -0.1739 0.2366 0.0321
2.750 0.7662 0.03543 0.02627 -0.1687 0.0357 0.0322
3.000 0.7925 0.03490 0.02563 -0.1693 0.0284 0.0324
3.250 0.8198 0.03432 0.02496 -0.1701 0.0269 0.0328
3.500 0.8467 0.03377 0.02432 -0.1707 0.0257 0.0334
3.750 0.8756 0.03305 0.02344 -0.1715 0.0244 0.0347
4.000 0.9004 0.03267 0.02296 -0.1715 0.0232 0.0351
4.250 0.9242 0.03238 0.02258 -0.1713 0.0223 0.0353
4.500 0.9478 0.03211 0.02220 -0.1709 0.0215 0.0357
4.750 0.9712 0.03186 0.02183 -0.1705 0.0210 0.0360
5.000 0.9956 0.03147 0.02126 -0.1701 0.0206 0.0372
5.250 1.0219 0.03078 0.02028 -0.1698 0.0204 0.0384
5.500 1.0414 0.03089 0.02028 -0.1686 0.0201 0.0386
5.750 1.0604 0.03107 0.02035 -0.1672 0.0199 0.0389
6.000 1.0788 0.03134 0.02052 -0.1658 0.0198 0.0392
6.250 1.0963 0.03172 0.02081 -0.1643 0.0195 0.0396
6.500 1.1134 0.03215 0.02116 -0.1627 0.0195 0.0408
6.750 1.1302 0.03266 0.02159 -0.1612 0.0193 0.0415
7.000 1.1463 0.03329 0.02220 -0.1595 0.0192 0.0416
7.250 1.1612 0.03400 0.02291 -0.1577 0.0191 0.0418
7.500 1.1757 0.03477 0.02371 -0.1559 0.0189 0.0419
7.750 1.1903 0.03561 0.02457 -0.1542 0.0189 0.0421
8.000 1.2045 0.03654 0.02553 -0.1524 0.0188 0.0422
8.250 1.2183 0.03755 0.02659 -0.1508 0.0187 0.0424
8.500 1.2322 0.03862 0.02772 -0.1491 0.0186 0.0427
8.750 1.2454 0.03976 0.02890 -0.1474 0.0185 0.0429
9.000 1.2581 0.04096 0.03014 -0.1457 0.0184 0.0431
9.250 1.2705 0.04218 0.03141 -0.1440 0.0182 0.0436
9.500 1.2822 0.04348 0.03276 -0.1422 0.0181 0.0446
9.750 1.2940 0.04478 0.03410 -0.1405 0.0178 0.0457
10.000 1.3057 0.04611 0.03548 -0.1388 0.0175 0.0464
10.250 1.3167 0.04750 0.03692 -0.1371 0.0173 0.0468
10.500 1.3280 0.04889 0.03835 -0.1354 0.0170 0.0471
10.750 1.3390 0.05033 0.03984 -0.1337 0.0169 0.0476
11.000 1.3499 0.05179 0.04135 -0.1321 0.0167 0.0481
11.250 1.3607 0.05329 0.04290 -0.1305 0.0167 0.0490
11.500 1.3718 0.05477 0.04443 -0.1289 0.0165 0.0505
11.750 1.3829 0.05628 0.04600 -0.1274 0.0165 0.0528
12.000 1.3939 0.05779 0.04756 -0.1259 0.0164 0.0567
12.250 1.4053 0.05928 0.04911 -0.1244 0.0163 0.0626
12.500 1.4211 0.06022 0.05103 -0.1241 0.0161 1.0000
12.750 1.4324 0.06171 0.05255 -0.1227 0.0161 1.0000
13.000 1.4438 0.06319 0.05407 -0.1212 0.0160 1.0000
13.250 1.4553 0.06468 0.05559 -0.1198 0.0159 1.0000
13.500 1.4669 0.06615 0.05711 -0.1184 0.0158 1.0000
13.750 1.4786 0.06762 0.05861 -0.1171 0.0157 1.0000
14.000 1.4918 0.06899 0.06008 -0.1157 0.0155 1.0000
14.250 1.5062 0.07027 0.06147 -0.1143 0.0152 1.0000
14.500 1.5215 0.07151 0.06283 -0.1129 0.0148 1.0000
14.750 1.5367 0.07281 0.06425 -0.1117 0.0144 1.0000
15.000 1.5511 0.07423 0.06579 -0.1104 0.0142 1.0000
15.250 1.5650 0.07575 0.06745 -0.1092 0.0140 1.0000
15.500 1.5780 0.07740 0.06925 -0.1080 0.0139 1.0000
15.750 1.5900 0.07922 0.07123 -0.1068 0.0137 1.0000
16.000 1.6003 0.08124 0.07343 -0.1056 0.0135 1.0000
16.250 1.6088 0.08347 0.07584 -0.1044 0.0133 1.0000
16.500 1.6151 0.08593 0.07850 -0.1033 0.0132 1.0000
16.750 1.6193 0.08863 0.08139 -0.1022 0.0131 1.0000
17.000 1.6217 0.09152 0.08448 -0.1012 0.0129 1.0000
17.250 1.6220 0.09462 0.08779 -0.1003 0.0128 1.0000
17.500 1.6207 0.09797 0.09134 -0.0996 0.0126 1.0000
17.750 1.6130 0.10291 0.09664 -0.0989 0.0123 1.0000
18.000 1.6018 0.10808 0.10213 -0.0987 0.0120 1.0000
18.250 1.5886 0.11339 0.10772 -0.0989 0.0118 1.0000
18.500 1.5734 0.11904 0.11363 -0.0997 0.0117 1.0000
18.750 1.5558 0.12523 0.12008 -0.1010 0.0116 1.0000
19.000 1.5356 0.13211 0.12721 -0.1032 0.0115 1.0000
19.250 1.5122 0.13996 0.13532 -0.1065 0.0114 1.0000
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Polar data table (+)
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